Patent ID: 7756612

Claim:
A method of piloting a rotorcraft having a plurality of engines and at least one lift and propulsion rotor, wherein so long as the rotorcraft has not reached an optimum climb speed (OCS), a pitch attitude control signal (Upitch) is determined that is adapted to cause the rotorcraft to acquire and maintain an acceleration (A 1 , A 2 , A 3 , A 4 ) that varies as a function of elapsed time in application of a determined acceleration profile (P 1 , P 2 , P 3 ), which profile varies as a function of the engine operating state (OEI/AEO); in which, after the pilot of the rotorcraft has engaged the corresponding automatic pilot mode, and during takeoff, so long as no engine is inoperative, a pitch attitude control signal is generated so that the acceleration of the rotorcraft follows a first profile or curve (P 1 ) including at least a first acceleration value (A 1 ) and a second acceleration value (A 2 ) distinct from the first acceleration value, wherein the acceleration of the rotorcraft is maintained substantially constant and equal to the first acceleration value for a first time interval and the second acceleration value for a second time interval, and in the event of an engine becoming inoperative, the pitch attitude control signal is generated in such a manner that the acceleration of the rotorcraft follows a second profile (P 2 ) distinct from the first profile, and including at least a third acceleration value (A 3 ) followed by a fourth acceleration value (A 4 ) distinct from the third acceleration value, wherein the acceleration of the rotorcraft is maintained substantially constant and equal to the third acceleration value for a first time interval calculated for the second profile (P 2 ) and the fourth acceleration value for a second time interval calculated for the second profile (P 2 ), with activation of the pitch attitude control being initiated by the pilot after a minimum safety height has been acquired relative to obstacles.