According to one embodiment, a rotorcraft (100) includes a main rotor system (110), an anti-torque rotor system, an anti-torque rudder system (200), and an anti-torque control system (300). The anti-torque rudder system (200) includes at least one rudder surface (210) operable to provide a second force on the body in the direction of rotation of the at least one main rotor blade (120). The anti-torque control system (300) is operable to receive a request to change an amount of anti-torque force applied to the body, compare a rotorcraft performance parameter to a threshold value, instruct one of the anti-torque rotor system or the anti-torque rudder system (200) to change the amount of the first force if the rotorcraft performance parameter is less than the threshold value, and, if the rotorcraft performance parameter is greater than the threshold value, instruct the other of the anti-torque rotor system or the anti-torque rudder system (200) to change the amount of the second force.
Rotorcraft anti-torque control system
Drehmomentausgleichssteuerungssystem für Drehflügler
Système de commande anticouple de giravion
2016-09-21
Patent
Elektronische Ressource
Englisch
IPC: | B64C AEROPLANES , Flugzeuge |