A vertical take-off and landing (VTOL) aircraft (10) comprises a fuselage (24) first and second forward wings (20, 22) and first and second rearward wings (30, 32), each wing having a fixed leading edge (25, 35) and a trailing control surface (50) which is pivotal about a generally horizontal axis. Electric rotors (60) are mounted to the wings (20, 22, 30, 32), the electric rotors (60) being pivotal with the trailing control surface (50) between a first position in which each rotor (60) has a generally vertical axis of rotation, and a second position in which each rotor (60) has a generally horizontal axis of rotation;wherein at least one of the wings (20, 22, 30, 32) has a first and a second electric rotor (60) which are each mounted having non-parallel axes of rotation so that the thrust lines of the first and second electric rotors are different.
WING TILT ACTUATION SYSTEM FOR ELECTRIC VERTICAL TAKE-OFF AND LANDING (VTOL) AIRCRAFT
FLÜGELNEIGUNGSBETÄTIGUNGSSYSTEM FÜR EIN ELEKTRISCHES SENKRECHT STARTENDES UND LANDENDES (VTOL) FLUGZEUG
SYSTÈME D'ACTIONNEMENT D'INCLINAISON D'AILE POUR AÉRONEF ÉLECTRIQUE À DÉCOLLAGE ET ATTERRISSAGE VERTICAUX (ADAV)
2024-06-26
Patent
Elektronische Ressource
Englisch
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