Patent ID: 8249792

Claim:
A method for protecting an aircraft comprising at least one wing-mounted engine arranged on each of its wings against at least one of a low-energy situation and a high-energy situation during flight in which at least one engine is a failed engine, the method comprising the steps of: detecting engine failure; measuring a plurality of parameters of said aircraft; triggering a control unit to activate a protection function, as a function of the number and position of failed engines, and control at least one non-failed engine of said aircraft, wherein the protection function is activated when activation conditions are met, with the activation conditions indicating that the aircraft is in the low-energy situation such that the total current power of the aircraft is less than a predetermined minimum power or that the aircraft is in the high-energy situation such that the total current power of the aircraft is greater than a predetermined maximum total power, wherein said triggering is carried out by a triggering unit, in which the triggering unit is configured to: A)—calculate a speed threshold of said aircraft from at least one of the measured parameters; and B)—determine from said calculated speed threshold, a total power to be applied to said engines of the aircraft in order to maintain the calculated speed threshold; and wherein said control unit is configured to: C)—determine, upon triggering by the triggering unit, a modification of power to each controlled non-failed engine such that a sum of the determined modified individual power to each of said controlled engines and of individual current power to each non-controlled engine is equal to the determined total power.