Patent ID: 8965603
Filing Date: 2015-02-24
Classification: B64D

Abstract:
1. A method for protecting an aircraft in flight phase, said aircraft exhibiting several configurations of slats and flaps and comprising means for measuring a normal acceleration of said aircraft, said method comprising: determining a current configuration of slats and flaps, determining, a limit angle of incidence beyond which the aircraft runs a risk of stalling, as a function of said current configuration of slats and flaps, determining a gain factor as a function of the measured normal acceleration of the aircraft, the gain factor variation as a function of the normal acceleration being predetermined and parameterizable, comparing a current angle of incidence of the aircraft with the limit angle of incidence weighted by the gain factor, the aircraft flying with said current configuration of slats and flaps, emitting an alert indicating that the aircraft runs a risk of stalling, if the current angle of incidence of the aircraft is greater than the limit angle of incidence weighted by the gain factor.