Changeable wing profile

Patent metadata

Field	Value
Publication number	US-9908611-B2
Application number	US-201414905102-A
Country	US
Kind code	B2
Filing date	Jul 10, 2014
Priority date	Jul 17, 2013
Publication date	Mar 6, 2018
Grant date	Mar 6, 2018

Abstract

This relates to changes in wing profiles. In order to provide an aerodynamic structure that can be variably adjusted and changed with respect to the wing profile, it is provided that an aerodynamic structure for a wing or rudder arrangement of an aircraft comprises a support structure and an outer skin. The support structure comprises an adaptive surface support structure in a longitudinal direction, which extends in a longitudinal direction from a root area to an outer end area, and is formed by a support surface, which comprises an adjustable periodic profiling that runs in the transverse direction, in which first flange areas and second flange areas are alternatingly formed, and joined together by web areas running in the direction of a profile height. Alternatingly aligned open profile segments running in the longitudinal direction are here formed.

First claim

What is claimed is:

1. An aerodynamic structure for a wing or rudder arrangement of an aircraft, comprising:
a support structure; and
an outer skin;
wherein the support structure comprises an adaptive surface support structure in the longitudinal direction, which extends in the longitudinal direction from a root area to an outer end area, and is formed by a support surface, which exhibits an adjustable periodic profiling that runs in a transverse direction, in which first and second flange areas are alternatingly formed, and joined together by web areas running in the direction of a profile height, wherein alternatingly aligned open profile segments running in the longitudinal direction are formed;
wherein, in the area of the open profile segments, the support structure comprises several connecting segments running in the transverse direction, which join together two adjacent first or second flange areas;
wherein at least a portion of the connecting segments are designed as adjustable-length connecting segments, so that the distance between the adjacent first or second flange areas can be adjusted;
wherein the width of the open profile segments can be varied by the adjustable connecting segments;
wherein the outer skin is attached to the support surface;
wherein an outer contour of the aerodynamic structure can be changed at least in the transverse direction by adjusting the distance between the adjacent first or second flange areas;
wherein the periodic profiling comprises a repeating sequence of flanges and webs and the alternatingly aligned opened profile segments; and
wherein the flange areas run on the two opposing outer sides of the profiling, with the first flange areas on one side and the second flange areas on the other side.

2. The aerodynamic structure of claim 1 , wherein the adjustable length connecting elements comprise actuating drives, actuating elements, guide elements or actuators.

3. The aerodynamic structure of claim 2 , wherein the periodic profiling comprises:
i) a trapezoidal profiling; and/or
ii) a wavelike profiling.

4. The aerodynamic structure of claim 3 , wherein the web areas and flange areas are interconnected in a longitudinal direction; and
wherein the profiling can be adjusted in the transverse direction in such a way that a width of the open profile segments can be varied by means of the adjustable connecting segments.

5. The aerodynamic structure of claim 4 , wherein at least one open profile segment comprises a spar, which extends in the longitudinal direction from a root area to an outer end area.

6. The aerodynamic structure of claim 5 , wherein the spar is integrated into the surface support structure.

7. The aerodynamic structure of claim 6 , wherein the surface support structure is connected to the spar in a central area of the surface support structure in such a way that adaptive areas of the surface support structure transverse to the longitudinal direction of the spar are formed on both sides of the spar.

8. The aerodynamic structure of claim 1 , wherein the outer skin can be shaped, and is attached to the surface support structure at least partially via hold points by means of retaining elements; and
wherein at least a portion of the retaining elements is designed as adaptive mounts, with which the location of the hold points in relation to the surface support structure can be varied.

9. The aerodynamic structure of claim 8 , wherein the adaptive mounts are adjustable-length hold members, with which the distance between the hold points and surface support structure can be adjusted.

10. The aerodynamic structure of claim 9 , wherein the outer skin is a single piece.

11. An aircraft, comprising:
a fuselage structure,
a wing assembly with at least one wing surface; and
a tail unit with at least one control surface;
wherein the wing assembly and tail unit are held on the fuselage structure; and
wherein at least one wing surface and/or one control surface is designed with an aerodynamic structure for a wing or rudder arrangement of an aircraft, comprising:
a support structure; and
an outer skin;
wherein the support structure comprises an adaptive surface support structure in the longitudinal direction, which extends in the longitudinal direction from a root area to an outer end area, and is formed by a support surface, which exhibits an adjustable periodic profiling that runs in a transverse direction, in which first and second flange areas are alternatingly formed, and joined together by web areas running in the direction of a profile height, wherein alternatingly aligned open profile segments running in the longitudinal direction are formed;
wherein, in the area of the open profile segments, the support structure comprises several connecting segments running in the transverse direction, which join together two adjacent first or second flange areas;
wherein at least a portion of the connecting segments are designed as adjustable-length connecting segments, so that the distance between the adjacent first or second flange areas can be adjusted;
wherein the width of the open profile segments can be varied by the adjustable connecting segments;
wherein the outer skin is attached to the support surface;
wherein an outer contour of the aerodynamic structure can be changed at least in the transverse direction by adjusting the distance between the adjacent first or second flange areas;
wherein the periodic profiling comprises a repeating sequence of flanges and webs and the alternatingly aligned opened profile segments; and
wherein the flange areas run on the two opposing outer sides of the profiling, with the first flange areas on one side and the second flange areas on the other side.

12. A method for adjusting an outer contour of an aerodynamic structure for a wing or rudder arrangement, comprising:
a) providing an aerodynamic structure for a wing or rudder arrangement of an aircraft; wherein the aerodynamic structure exhibits a support structure and an outer skin; and
wherein the support structure exhibits an adaptive surface support structure in the longitudinal direction, which extends in a longitudinal direction from a root area to an outer end area, and is formed by a supporting surface, which exhibits an adjustable periodic profiling that runs in a transverse direction, in which first and second flange areas are alternatingly formed, and joined together by web areas running in the direction of a profile height, wherein alternatingly aligned open profile segments running in the longitudinal direction are here formed; wherein, in the area of the open profile segments, the support structure exhibits several connecting segments running in the transverse direction, which join together two adjacent first or second flange areas; and wherein at least a portion of the connecting segments are designed as adjustable-length connecting segments; and wherein the outer skin is attached to the supporting surface;
wherein the periodic profiling comprises a repeating sequence of flanges and webs and the alternatingly aligned opened profile segments; and
wherein the flange areas run on the two opposing outer sides of the profiling, with the first flange areas on one side and the second flange areas on the other side;
b) adjusting the adjustable-length connecting segments, wherein a width of the open profile segments in varied by the adjustable connecting segments; and
c) changing the outer contour of the aerodynamic structure at least in the transverse direction.

Assignees

• Airbus Defence & Space Gmbh

Inventors

• Haslach Horst

Classifications

• B64C9/00

  Adjustable control surfaces or members, e.g. rudders (trimming stabilising surfaces B64C5/10) · CPC title

• B64C3/44 Primary

  Varying camber · CPC title

• Y02T50/145

  Cross-Sectional Technologies · mapped topic

• B64C3/185

  Spars · CPC title

• B64C2003/445

  by changing shape according to the speed, e.g. by morphing · CPC title