Patent ID: 8738199

Claim:
A method for dramatically reducing the take-off run of an aircraft (AC), wherein the aircraft (AC) comprises at least one piloting stick ( 14 ), a main landing gear ( 11 ), ailerons ( 6 G, 6 D), and depth moving aerodynamic surfaces ( 7 , 9 G, 9 D), wherein the method is implemented in flight control calculators of said aircraft (AC), provided with information about the tilting (β) of said piloting stick ( 14 ) and the attitude (θ) of said aircraft (AC), wherein the take-off run is a period during which said aircraft (AC) is running on a take-off runway (RW) by accelerating with said main landing gear ( 11 ) compressed by the mass of said aircraft and by ground effect and with said ailerons ( 6 G, 6 D) occupying a position (α D ) partly deflected downwards to maximize the fineness ratio of said aircraft, wherein a tilting threshold (Sβ) is at least equal to a take-off tilting (β 0 ) usually used during a regular take-off, the method comprising: tilting said piloting stick ( 14 ) in the nose up direction to deflect said depth aerodynamic surfaces ( 7 , 9 G, 9 D) upwards to provide said aircraft with a high value attitude (θ c ) at which the tail of said aircraft approaches but does not strike the take-off runway (RW); setting a stick criterion (Cβ) the value of which is 0 below said tilting threshold (Sβ) and the value of which increases from 0 to 1 between said tilting threshold (Sβ) and a controlled tilting value (β c ) close to, but lower than, the maximum nose-up tilting (β m ) of said stick; setting an attitude criterion (Cθ), the value of which is 0 below said attitude threshold (Sθ) and the value of which increases from 0 to 1 between said attitude threshold (Sθ) and a controlled attitude value (θ c ) close to, but lower than, a tail strike attitude (θ TS ), at which the tail of said aircraft would strike the runway; setting, an aileron deflection criterion from the greater of the stick criterion (Cβ) and the attitude criterion (Cθ), wherein the aileron deflection criterion steadily increases from the value (α D ) corresponding to the partly deflected position downwards to the value (α M ) corresponding to the fully deflected position downwards, when said greater criterion switches from the value of 0 to the value of 1; after said deflection upwards and while said main landing gear ( 11 ) is still compressed, fully deflecting said ailerons ( 6 G, 6 D) downwards (α M ), symmetrically, from their position (α D ) partly deflected downwards; continuing acceleration of the aircraft until take-off, while maintaining the high value attitude (θ c ) position and while maintaining said ailerons ( 6 G, 6 D) fully deflected downwards.