Changeable wing profile

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 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, each comprising a plurality of strung together triangular compartments that are formed by fixed-length guide elements and adjustable-length guide 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-length guide 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 framework segments;
• wherein the adjustable-length guide elements are active actuating drives;
• and
• wherein the adjustable-length guide elements in the triangular compartments are arranged such that each triangular compartment comprises an adjustable-length guide element facing the outside, wherein the triangular compartments are arranged such that adjustable-length guide elements are provided on alternating upper and lower sides of the aerodynamic structure.

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;
• 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, each comprising 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 joined to the fixed spar, and the outer skin is held by the framework segments;
• and wherein at least one side of at least a portion of the triangular compartments comprises one of the adjustable-length 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;
• and wherein the adjustable-length guide elements are active actuating drives;
• and wherein the adjustable-length guide elements in the triangular compartments are arranged such that each triangular compartment comprises an adjustable-length guide element facing the outside, wherein the triangular compartments are arranged such that adjustable-length guide elements are provided on alternating upper and lower sides of the aerodynamic structure;
• b) actively adjusting the adjustable-length guide elements;
• and
• c) changing the outer contour of the aerodynamic structure at least in the transverse direction.

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, each comprising a plurality of strung together triangular compartments that are formed by fixed-length guide elements and adjustable-length guide 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-length guide 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 framework segments;
• 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;
• wherein the adjustable-length guide elements are active actuating drives;
• and
• wherein the adjustable-length guide elements in the triangular compartments are arranged such that each triangular compartment comprises an adjustable-length guide element facing the outside, wherein the triangular compartments are arranged such that adjustable-length guide elements are provided on alternating upper and lower sides of the aerodynamic structure.