An anti-torque system (120) for a rotorcraft (10) includes a first tail fan assembly (124) including a plurality of first fan blades (136), a second tail fan assembly (122) including a plurality of second fan blades (134) and a motor (130, 132) adapted to provide torque to the first (136) and second (134) fan blades. The first fan blades (136) have a larger rotational inertia than the second fan blades (134). The second fan blades (134) are adapted to experience a larger angular acceleration than the first fan blades (136) in response to torque from the motor (130, 132), thereby providing responsive yaw control for the rotorcraft (10).
ANTI-TORQUE SYSTEMS FOR ROTORCRAFT
DREHMOMENTAUSGLEICHSSYSTEME FÜR DREHFLÜGLER
SYSTÈMES ANTICOUPLE POUR GIRAVION
2020-09-09
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge |