Morphing trailing edge device for an airfoil

A morphing airfoil for an aircraft comprising a morphing trailing edge device comprising:

• a skin member;
• an actuator;
• and
• a torsion element,
• wherein the skin member is configured to extend on a surface of a trailing edge region of an airfoil and comprises a load introduction point within a reinforced area,
• wherein the skin member further comprises a stiffening member arranged essentially perpendicular to a load introduction direction in the load introduction point,
• wherein the load introduction point, the reinforced area and the stiffening member are integrated into the skin member,
• wherein the actuator is configured to drive the torsion element with an actuation load,
• wherein the torsion element is configured to translate the actuation load to the load introduction point, so that the actuation load morphs the trailing edge region in a first or a second side of a plane, and
• wherein the airfoil is a winglet, a vertical stabilizer, a horizontal stabilizer, a spoiler or a flap of an aircraft.

A method for manufacturing a morphing airfoil for an aircraft, the method comprising:

• providing a skin member comprising a load introduction point within a reinforced area and a stiffening member arranged essentially perpendicular to a load introduction direction in the load introduction point;
• extending the skin member on a surface of a trailing edge region of an airfoil;
• providing a torsion element;
• and
• providing an actuator configured to drive the torsion element with an actuation load,
• wherein the load introduction point, the reinforced area and the stiffening member are integrated into the skin member, and
• wherein the torsion element is configured to translate the actuation load to the load introduction point, so that the actuation load morphs the trailing edge region up- or downwardly relative to a horizontal plane.