Patent ID: 7720578

Claim:
A method of controlling of an aircraft in terms of pitch, according to which method the following series of successive steps is carried out, in an automatic and repetitive manner: a) a controlled load factor NZc is taken into account; b) a load factor NZcg applied to the aircraft is estimated; c) a control command is calculated by taking into account at least the following main expression: K1·NZc+K2·NZcg K1 and K2 being two predetermined gain values; and d) this control command is transmitted to a deflection means ( 5 ) of at least one rudder ( 7 ) of the aircraft, said deflection means ( 5 ) generating a deflection command representative of said control command and transmitting it to at least one actuator ( 9 ) of said rudder ( 7 ), wherein the following series of successive steps is carried out in addition, in an automatic and repetitive manner, before said step c): the actual Mach number of the aircraft is determined; the actual angle of incidence of the aircraft is determined; said actual angle of incidence is compared to an angle-of-incidence reference value; and if said actual angle of incidence is greater than said reference value, a modified gain value ΔK2 is determined with the aid of said actual Mach number and of said actual angle of incidence, said modified gain value ΔK2 replacing said gain value K2 in the calculation of said control command in said step c).