Abstract: An aircraft having a reduced-load wing structure is provided with a controllable canard stabilizer (5G, 5D) at the front end of the aircraft and a controller that controls the canard stabilizer. The controller generates a turn command corresponding to an increase in the lift of the canard stabilizer when, simultaneously, the turn command applied by the pilot to the elevational control surfaces (6G, 6D) exceeds a threshold and the measurement of the vertical acceleration of the aircraft exceeds a threshold.

Abstract: Airplane (1) including a mainplane (3), elevator aerodynamic surfaces (4) and a front canard empennage adjustable in orientation. This airplane includes:a device for calculating (14) continuously receiving measurements:of the speed (V) of the airplane with respect to the air,of the centering (c) of the airplane (1),of the flight altitude (H), andof the mass (m) of said airplane and calculating the angular setting to be given to said planes (5) of the canard empennage, during phases of stabilized flight without atmospheric disturbances, so that the lift of said canard empennage corresponds, at any moment, to the smallest possible value of the drag of the airplane; and a device (9) forconferring an at least substantially constant lift on said empennage when the airplane in flight is not in a phase of stabilized flight without atmospheric disturbances.

Abstract: According to the invention, attenuator means (8) are provided, making it possible to limit the rate of rotation of the airplane on takeoff, so as to avoid the tail of the airplane striking the ground and to reduce the dispersion of the rotation rates.