Abstract: A method for aiding the landing of an aircraft on a landing runway comprising the following steps implemented in an automatic manner by a processing unit: a) acquiring information relating to the landing runway; b) acquiring information relating to a current situation of the aircraft; f) determining a maximum roll angle, in absolute value, necessary to allow a flight of the aircraft along a trajectory between a current position and a target landing position on the landing runway; g) comparing this maximum roll angle with a predetermined limit; and h) as a function of the result of the comparison carried out in step g), commanding, if appropriate, the signaling of an alert by means of a signaling system of the aircraft.

Abstract: A method for aiding the landing of an aircraft on a landing runway comprises the following steps implemented automatically by a processing unit: a) acquiring information relating to the runway; b) acquiring information relating to a current situation of the aircraft; i) determining a landing position of the aircraft on a central longitudinal axis of the runway, as a function of a trajectory determined between a current position of the aircraft and this landing position to comply with at least one constraint relating to a roll angle of the aircraft; j) determining a parameter relating to the landing position; k) determining a deviation between this parameter and a reference value; l) comparing this deviation with a predetermined threshold; and m) as a function of the result of the comparison carried out in step l), commanding, if appropriate, the signaling of an alert via the signaling system of the aircraft.

Abstract: A method for aiding the landing of an aircraft on a landing runway comprises the following steps implemented in an automatic manner by a processing unit: a) acquiring information relating to the landing runway; b) acquiring information relating to a current situation of the aircraft; c) determining, as a function of said information, at least one deviation between at least one parameter relating to a landing position of the aircraft on the landing runway and a reference relating to a central longitudinal axis of the landing runway; d) comparing this deviation with a predetermined threshold; and e) as a function of the result of the comparison carried out in step d), commanding, if appropriate, the signaling of an alert by means of a signaling system of the aircraft.

Abstract: A slip-reduction control unit for an aircraft having a steerable landing gear. The control unit receives steering input signals from which a target steering command output may be ascertained and additional input signals (a) the motion of the aircraft, (b) a steering angle, or (c) a parameter relating to the slip sustained by the steerable landing gear. The slip-reduction control unit determines, based on the additional input signals, reduces the rate of change of steering angle that would otherwise be commanded. The reduction in the rate of change may reduce vibration on the aircraft that might be caused by a greater rate of change in the steering angle.

Abstract: A method and device for aiding piloting of an aircraft, during at least one flight phase including piloting steps. The device includes a unit for real-time acquisition of flight parameters of the aircraft, a calculation unit for calculating in real time with the parameters, for each of the piloting steps, a distance between current position of the aircraft and a position along a flight trajectory followed by the aircraft, at which the aircraft will reach the corresponding piloting step. At least one display unit is provided for displaying, in real time, characteristic signs each illustrating one of the piloting steps, the characteristic signs being integrated into the environment viewed with the aid of the screen and being positioned so as to make it possible to locate a place of the environment along the flight trajectory followed by the aircraft, at which the aircraft will reach the piloting step.

Abstract: A control system and method for an aircraft configured to operate according to a first mode of operation corresponding to an automatic piloting of the aircraft and a second mode of operation corresponding to a manual piloting of the aircraft, the system including a selection member. The system is configured to operate according to the first mode of operation when the selection member is not actuated continuously and to operate according to the second mode of operation when the selection member is actuated continuously.

Abstract: The device includes, but is not limited to a calculating unite for automatically applying, if conditions for turning of the aircraft are met, a symmetrical braking value at a brake assembly, then in the course of the turn automatically distributing this symmetrical braking value in differential braking between braking device of the left main landing gear and braking device of the right main landing gear of the aircraft, as a function of current directional command orders, in such a way as to maintain a constant overall braking level, at least for directional command orders below a predetermined threshold.