An anti-torque system for a rotorcraft includes a first tail fan assembly including a plurality of first fan blades, a second tail fan assembly including a plurality of second fan blades and a motor 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 motor, thereby providing responsive yaw control for the rotorcraft.
Anti-Torque Systems for Rotorcraft
2020-05-21
Patent
Elektronische Ressource
Englisch
IPC: | B64C AEROPLANES , Flugzeuge |