A propulsion system (20) for a rotorcraft (10) includes a first fan assembly (22) including a plurality of first fan blades (30), a second fan assembly (24a, 24b, 24c, 24d) including a plurality of second fan blades (34a, 34b, 34c, 34d) and a drive system adapted to provide torque to the first (30) and second fan blades (34a, 34b, 34c, 34d). The first fan blades (30) have a larger rotational inertia than the second fan blades (34a, 34b, 34c, 34d). The second fan blades (34a, 34b, 34c, 34d) are adapted to experience a larger angular acceleration than the first fan blades (30) in response to torque from the drive system, thereby providing responsive thrust control for the rotorcraft (10).
ROTORCRAFT AND PROPULSION SYSTEMS FOR ROTORCRAFT
DREHFLÜGLER AND ANTRIEBSSYSTEME FÜR DREHFLÜGLER
GIRAVION AND SYSTÈMES DE PROPULSION POUR GIRAVION
23.09.2020
Patent
Elektronische Ressource
Englisch
IPC: | B64C AEROPLANES , Flugzeuge |