Changeable wing profile

Patent metadata

Field	Value
Publication number	US-2016159456-A1
Application number	US-201414905109-A
Country	US
Kind code	A1
Filing date	Jul 10, 2014
Priority date	Jul 17, 2013
Publication date	Jun 9, 2016
Grant date	—

Abstract

This relates to changes in wing profiles. In order to make available 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 a fixed spar in the longitudinal direction, which extends from a root area to an outer end area. The support structure also comprises several adaptive framework segments in the transverse direction, which each consist of a plurality of strung together triangular compartments, which are formed by fixed-length guide elements and adjustable-length guide elements The framework segments are joined to the fixed spar. At least one side of a portion of the triangular compartments comprises one of the adjustable guide elements, so that the shape of the framework segments can be adjusted.

First claim

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 a fixed spar in the longitudinal direction, which extends from a root area to an outer end area; wherein the support structure comprises several adaptive framework segments in the transverse direction, which each consist of a plurality of strung together triangular compartments that are formed by fixed-length guiding elements and adjustable-length guiding elements; wherein the framework segments are joined to the fixed spar; wherein least one side of at least a portion of the triangular compartments comprises one of the adjustable guiding elements, so that the shape of the framework segments can be adjusted; wherein the outer skin is held by the framework segments; wherein an outer contour of the aerodynamic structure can be changed at least in the transverse direction by adjusting the shape of the frameworks.

2 . The aerodynamic structure of claim 1 , wherein the framework segments are joined to the fixed spar transversely to its longitudinal direction in such a way as to provide triangular compartments on both sides of the spar.

3 . The aerodynamic structure of claim 2 , wherein it is provided that fixed guide elements are continuously strung together in the direction of the framework segment.

4 . The aerodynamic structure of claim 3 , wherein the adjustable guide elements in the triangular compartments are arranged in such a way that each triangular compartment comprises an adjustable guide element on the side facing the outside.

5 . The aerodynamic structure of claim 4 , wherein the spar forms a longitudinal beam, to which several framework segments are sequentially attached as transverse ribs.

6 . The aerodynamic structure of claim 5 , wherein several framework segments are arranged parallel to each other, and run parallel to the flight direction.

7 . The aerodynamic structure of claim 6 , wherein the aerodynamic structure forms a front edge on a longitudinal edge, and
wherein the end area of the framework segments that faces the front edge is designed with a fixed, triangular compartment.

8 . The aerodynamic structure of claim 7 , wherein the fixed spar comprises a triangular cross section, and has three longitudinal edges,
wherein the triangular cross section of the spar is integrated into the framework segments; and wherein it is provided that the fixed or adjustable guide elements be attached to the three longitudinal edges.

9 . The aerodynamic structure of claim 8 , wherein the outer skin can be shaped, and is attached to the framework segments at least partially via hold points by 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 framework segments can be varied.

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

11 . The aerodynamic structure of claim 10 , wherein the outer skin consists of a single piece.

12 . 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.

13 . A method for adjusting an outer contour of an aerodynamic structure for a wing or rudder arrangement, which comprises the following steps:
a) providing an aerodynamic structure for a wing or rudder arrangement of an aircraft; and wherein the aerodynamic structure comprises a support structure and an outer skin; and wherein the support structure comprises a fixed spar in the longitudinal direction, which extends from a root area to an outer end area; and wherein the support structure comprises several adaptive framework segments in the transverse direction, which each consist of a plurality of strung together triangular compartments, which are formed by fixed-length guide elements and adjustable-length guide elements; and wherein the framework segments are connected to the fixed spar, and the outer skin is attached to the framework segments; and wherein at least one side of at least a portion of the triangular compartments comprises one of the adjustable guide elements, so that the framework segments have an adjustable shape; and wherein adjusting the shape of the framework segments makes it possible to vary the outer contour of the aerodynamic structure, at least in the transverse direction; b) adjusting the adjustable-length guide elements; and c) changing the outer contour of the aerodynamic structure at least in the transverse direction.

14 . (canceled)

Assignees

• Airbus Defence & Space Gmbh

Inventors

• Haslach Horst

Classifications

• B64C13/24

  Transmitting means · CPC title

• B64C9/00

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

• B64C3/48 Primary

  by relatively-movable parts of wing structures · CPC title

• Y02T50/10

  Drag reduction · CPC title