FLIGHT CONTROL SYSTEM AND METHOD IN DIRECTIONAL STABILITY OR HEADING MODE IN A ROTARY WING AIRCRAFT BASED ON ITS FORWARD SPEED

摘要

The present invention relates to a method and a flight control system (1) for rotary wing aircraft (10). A first mode of operation of said method makes it possible, when the longitudinal speed U x of said aircraft (10) is greater than a first threshold speed V threshold1, to perform a flight with a trajectory holding relative to the ground, the flight instructions of an autopilot (15) being a soil ground angle TK ground, a forward speed Va, a slope P and a heading .PSI .. A second operating mode allows, when said longitudinal velocity U x is less than one second threshold speed V only, to perform a flight with a heading behavior, said flight instructions being said longitudinal velocity U x, a lateral velocity VY, a vertical velocity W z and said heading .PSI ..