A propulsion system for a rotorcraft includes a first fan assembly including a plurality of first fan blades, a second fan assembly including a plurality of second fan blades and a drive system adapted to provide torque to the first and second fan blades. The first fan blades have a larger rotational inertia than the second fan blades. The second fan blades are adapted to experience a larger angular acceleration than the first fan blades in response to torque from the drive system, thereby providing responsive thrust control for the rotorcraft.
Propulsion Systems for Rotorcraft
05.09.2019
Patent
Elektronische Ressource
Englisch
IPC: | B64C AEROPLANES , Flugzeuge |