Method and device for determining the dynamic stability margin of an aircraft

SD MP CG O SD MP O ααMPA method of determining a dynamic stability margin Mof an aircraft includes calculating the longitudinal position Xof a maneuver point MP to find the distance between the maneuver point and the position Xof the aircraft center of gravity CG, as a function of the angular velocity ωof an incidence oscillation of the aircraft. A device for determining the dynamic stability margin Mor a position Xof the maneuver point MP includes means or acquisition of data and or calculating a dynamic stability margin. The means receive data for generating, the aircraft mass m and pitch inertia Iyy; the flight speed V; the angular velocity ωof the incidence oscillation at a flight point; a coefficient C* representing Cz of a "quasi-static" model of the aircraft. The aircraft flight control laws may be adapted according to the stability margin and to X.