An aircraft comprising an airframe; a rotor system mounted to the airframe, the rotor system including a plurality of rotor blades, each of the plurality of rotor blades including a root portion extending to a tip portion through an airfoil portion, the airfoil portion having a leading edge and a trailing edge; at least one control surface mounted within the airfoil portion of at least one of the plurality of rotor blades; at least one actuator configured to actuate the at least one control surface; and at least one actuator configured to pitch at least one of the plurality of rotor blades about a blade pitch axis
REDUCED POWER INDIVIDUAL BLADE CONTROL SYSTEM ON A ROTORCRAFT
INDIVIDUELLES BLATTSTEUERUNGSSYSTEM MIT REDUZIERTER LEISTUNG AUF EINEM DREHFLÜGLER
SYSTÈME DE COMMANDE DES PALES INDIVIDUELLES À PUISSANCE RÉDUITE SUR UN GIRAVION
2020-01-29
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge |
REDUCED POWER INDIVIDUAL BLADE CONTROL SYSTEM ON A ROTORCRAFT
European Patent Office | 2017
|Actuator Saturation in Individual Blade Control of Rotorcraft
British Library Conference Proceedings | 2012
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