Patent ID: 6453221
Filing Date: 2002-09-17
Classification: G05D

Abstract:
A method for determining, on an aircraft equipped with a plurality of engines, a minimum control speed with at least one engine shut down, said method comprising the steps of:(a) measuring, during at least one flight of said aircraft, values of predefined parameters on said aircraft, (b) determining, on the basis of said measurements and at least one predefined certification value, a certification value (Cnfcertif) for a yaw moment (Cnf) created by a shutting down of said at least one engine; (c) calculating, on the basis of said certification value (Cnfcertif), a value of a parameter (K) to allow forming of a first relationship: &Dgr;fn=K.Vc2, in which:&Dgr;fn illustrates a asymmetry of thrust due to the shutting down of the at least one engine; and Vc represents a speed of the aircraft; and (d) determining, on the basis of said first relationship and of engine thrust curves, said minimum control speed, wherein step (b) comprises: (i) deducing, on the basis of simultaneously measured values of, respectively, the sideslip (&bgr;) and the lateral force (Cy), a second relationship between said sideslip (&bgr;) and said lateral force (Cy) is deduced; (ii) determining, on the basis of said second relationship and a certification value (Cycertif) of said lateral force (Cy), a corresponding certification value (&bgr;certif) for the sideslip (&bgr;); (iii) deducing, on the basis of the simultaneously measured values of , respectively, said sideslip (&bgr;), said lateral force (Cy) and said yaw moment (Cnf), a third relationship between said sideslip (&bgr;), said lateral force (Cy) and said yaw moment (Cnf); and (iv) determining said certification value (Cnfcertif) on the basis of said third relationship and said certification values (Cycertif) and (&bgr;certif).