A method of automatically adjusting lift in a hybrid rotorcraft, the hybrid rotorcraft including a fuselage and at least two half-wings on either side of the fuselage, the at least two half-wings including at least one left half-wing having a left fixed structure secured to the fuselage and at least one left flap mounted to move relative to the left fixed structure, and at least one right half-wing having a right fixed structure secured to the fuselage and at least one right flap mounted to move relative to the right fixed structure. The method determines at least one first deflection angle setpoint δw1 by which the at least one left flap is to be deflected relative to the left fixed structure and at least one second deflection angle setpoint δw2 by which the at least one right flap is to be deflected relative to the right fixed structure.
PROCEDE D'AJUSTEMENT AUTOMATIQUE D'UNE PORTANCE D'UN GIRAVION HYBRIDE ET UN GIRAVION HYBRIDE ASSOCIE
METHOD FOR AUTOMATICALLY ADJUSTING A HYBRID ROTORCRAFT LIFT AND ASSOCIATED HYBRID ROTORCRAFT
VERFAHREN ZUR AUTOMATISCHEN REGULIERUNG DES AUFTRIEBS EINES HYBRIDEN DREHFLÜGELFLUGZEUGS UND ENTSPRECHENDES HYBRIDES DREHFLÜGELFLUGZEUG
2022-07-13
Patent
Electronic Resource
French
IPC: | B64C AEROPLANES , Flugzeuge |
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