Patent ID: 8340840

Claim:
A method for attenuating on an aircraft (A) the side effects generated by at least one turbulence event undergone by this aircraft (A) upon a flight, method according to which, upon a flight of aircraft (A), automatically and iteratively, comprising: a) estimating a roll moment of aircraft (A), which is due to wind and a yaw moment of the aircraft (A), which is also due to wind; b) measuring the current values of aircraft (A); c) using said estimated roll moment, said yaw moment and said measured current values, calculating: a roll control command for at least one first controllable movable member ( 20 , 21 ) which is likely to act on the roll of aircraft (A), said roll control command being such that, as applied to said first movable member ( 20 , 21 ), it enables the roll disturbances due to wind to be minimised on aircraft (A); and a yaw control command for at least one second controllable movable member ( 22 ) which is likely to act on the yaw of aircraft (A); and d) applying: said roll control command to said first movable member ( 20 , 21 ); and said yaw control command to said second movable member ( 22 ), a method according to which, further at step c): said roll control command δl and said yaw control command δr are calculated, using the following mathematical expression: [ δ ⁢ ⁢ l δ ⁢ ⁢ r ] = ( C ⁢ ⁢ l ⁢ ⁢ δ ⁢ ⁢ l C ⁢ ⁢ l ⁢ ⁢ δ ⁢ ⁢ r C ⁢ ⁢ n ⁢ ⁢ δ ⁢ ⁢ l C ⁢ ⁢ n ⁢ ⁢ δ ⁢ ⁢ r ) - 1 ⁡ [ Δ ⁢ ⁢ C ⁢ ⁢ l ⁢ ⁢ w Δ ⁢ ⁢ C ⁢ ⁢ n ⁢ ⁢ w ] wherein: Clδl and Clδr are roll moment coefficients; Cnδl and Cnδr are yaw moment coefficients; ΔClw is said roll moment due to wind; and ΔCnw is said yaw moment due to wind; and said yaw control command is calculated so that, when applied to said second movable member ( 22 ), said yaw control command enables both the side effects generated by the turbulence event and the side effects generated by applying said roll control command to said first movable member ( 20 , 21 ) to be compensated for on aircraft (A).