Abstract: The invention describes a wind turbine rotor blade active flap (1) comprising a primary body (1P) adapted for mounting to the trailing edge (20TE) of a wind turbine rotor blade (20); a flap turning means (10, 11, 12) adapted to turn the active flap (1) between a neutral position (R0), in which the active flap (1) directs airflow (A20S, A20P) towards the suction side (P20S) of the rotor blade (20), and a working position (R-Rmax), in which the active flap (1) directs airflow (A20S, A20P) towards the pressure side (P20P) of the rotor blade (20); and a secondary body (1S) mounted to the primary body (1P) and configured to hold the active flap (1) in its neutral position (R0). The invention further describes a wind turbine (2) comprising a number of rotor blades (20) mounted to a hub; and an active flap (1) according to the invention, mounted to the trailing edge (20TE) of each rotor blade (20).

Abstract: A method of controlling a wind turbine having a tower and a rotor at which plural rotor blades are mounted includes: determining, in particular in real time, a damping characteristic of at least one vibration mode related to the wind turbine; and controlling the wind turbine based on damping characteristic.

Abstract: A method of controlling a wind turbine having a tower and a rotor at which plural rotor blades are mounted includes: determining, in particular in real time, a damping characteristic of at least one vibration mode related to the wind turbine; and controlling the wind turbine based on damping characteristic.

Abstract: An aircraft includes the aircraft component. The aircraft component includes an outer skin portion, a plurality of major stiffeners, and a plurality of minor stiffeners. The outer skin portion has an interior side and an exterior side configured to define an exterior boundary of the aircraft. The major stiffeners are integral with the outer skin portion and extend out from the interior side. The major stiffeners are configured to resist global deflection of the aircraft component in response to a bird strike on the aircraft component. The minor stiffeners are disposed between the major stiffeners, are integral with the outer skin portion, and extend out from the interior side. The minor stiffeners are configured to resist perforation of the aircraft component in response to the bird strike on the aircraft component.

Abstract: Aircraft components and aircraft are provided. An aircraft includes the aircraft component. The aircraft component includes an outer skin portion, a plurality of major stiffeners, and a plurality of minor stiffeners. The outer skin portion has an interior side and an exterior side configured to define an exterior boundary of the aircraft. The major stiffeners are integral with the outer skin portion and extend out from the interior side. The major stiffeners are configured to resist global deflection of the aircraft component in response to a bird strike on the aircraft component. The minor stiffeners are disposed between the major stiffeners, are integral with the outer skin portion, and extend out from the interior side. The minor stiffeners are configured to resist perforation of the aircraft component in response to the bird strike on the aircraft component.