In accordance with an embodiment, a method of operating a rotorcraft (101) includes transitioning from a first mode to a second mode when a velocity of the rotorcraft (101) exceeds a first velocity threshold. Transitioning between the first and second modes includes fading out a gain of a dynamic controller over a first period of time, and decreasing a value of an integrator of the dynamic controller over a second period of time. In the first mode, the translational speed of the rotorcraft (101) is determined based on a pilot stick signal, and in the second mode, an output of an attitude rate controller is proportional to an amplitude of the pilot stick signal
ROTORCRAFT CONTROL MODE TRANSITION SMOOTHING
DREHFLÜGLERSTEUERMODUSÜBERGANGSGLÄTTUNG
LISSAGE DE LA TRANSITION DU MODE DE COMMANDE D'UN GIRAVION
2019-04-17
Patent
Electronic Resource
English