An aircraft comprises a fuselage, a wing (2) attached to the fuselage, a wing tip device (6) attached to a wing end (4) of the wing (2), at least one additional wing-like element (14) having a wing root (22), a wing leading edge (18) and a wing trailing edge (20), and a torque control device having a rotatable interface means. The torque control device is adapted for rotatably supporting the wing root of the wing-like element on the interface means under creation of a rotational axis (16) extending from the interface means into the wing-like element (14), about which rotational the wing-like element (14) is rotatable. The wing-like element (14) is adapted to induce a rotation around the rotational axis (16) in an air flow. The torque control device is adapted to limit the degree of rotation depending on a torque introduced into the interface means by the wing-like element (14) and the wing root (22) of the at least one wing-like element (14) is coupled with at least one of the wing tip device (6), the wing (2) and the fuselage through the torque control device such that the leading edge (18) extends into an airflow surrounding the aircraft.
AIRCRAFT WITH LOAD REDUCING WING LIKE ELEMENT
FLUGZEUG MIT LASTVERRINGERNDEM FLÜGELARTIGEM ELEMENT
AÉRONEF ÉQUIPÉ D'UN ÉLÉMENT DE TYPE AILE DE RÉDUCTION DE CHARGE
2020-12-23
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge |
AIRCRAFT WING LOAD REDUCTION DEVICE AND AIRCRAFT WING LOAD REDUCTION METHOD
European Patent Office | 2019
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