Patent ID: 7942370

Claim:
A method for an aircraft provided with an electric flight control system to improve flight in disturbed air, the method comprising: receiving a current airflow direction signal from an angle-of-attack sensor; creating a synthetic angle-of-attack signal that is more calm than the current airflow direction signal received from the angle-of-attack sensor; using said airflow direction signal and the synthetic angle-of-attack signal to form a wake vortex level signal representative of a current wake vortex level of the air meeting the aircraft; testing a magnitude of said wake vortex signal; deciding based on said magnitude, if the aircraft is passing through wake vortex disturbed air or not; if the aircraft is judged to pass trough vortex disturbed air, switching from a normal way of flight control to an alternative way of flight control; and deciding, based on said magnitude, when wake vortex is passed, and if so switch back to the normal way of flight control, wherein the switching from a normal way of flight control to an alternative way of flight control includes switching angle-of-attack input signal from what is measured by the angle-of-attack sensor to the synthetic angle-of-attack signal when the aircraft passes into vortex disturbed air, and vice versa when the aircraft has entered non-disturbed air again.