Abstract: A system for assisting in managing the flight of an aircraft in a landing phase. The system comprises a trajectory computation module for determining a trajectory of the aircraft, an interface module and an auxiliary computation module for computing an optimized ground slope, a display unit for allowing an operator to make a selection of the optimized ground slope, and a guidance unit for transmitting guidance orders to controls of the aircraft, the system being configured for the aircraft to follow the optimized ground slope when the latter is selected by the interface module, such that the aircraft reaches a target vertical speed on initiation of the flare phase of the landing.

Abstract: A device aiding the flight management of an aircraft during a phase of landing on an airport includes means for automatically determining an adaptive aiming point that is shifted along the runway in the downstream direction and which can be used by different usual landing aid means of the aircraft.

Abstract: A target vertical speed, to be applied to the aircraft upon the initiation of the aircraft's flaring phase, is defined in relation to the ground. An optimized ground slope associated with an approach path to be tracked during the landing, is then determined as a function of the determined target vertical speed and of at least one outside parameter. This optimized ground slope is at least equal to a predefined ground slope. Upon interception by the aircraft with the approach path, the aircraft is guided to track the determined optimized ground slope associated with the approach path and reach the target vertical speed upon initiation of the flaring phase.

Abstract: A device aiding the flight management of an aircraft during a phase of landing on an airport includes means for automatically determining an adaptive aiming point that is shifted along the runway in the downstream direction and which can be used by different usual landing aid means of the aircraft.

Abstract: According to the invention, the engine pylon for the suspension of a turbo engine under an aircraft wing is such that the trailing edge of the rear lower part of the engine pylon is shifted toward the root of the wing.

Abstract: According to the invention, a target vertical speed (Vzo), defined in relation to the ground, is determined and an optimized ground slope (?o), associated with an approach path (A) to keep track during the landing, is determined on the basis of said determined target vertical speed (Vzo) and of at least one outside parameter, said optimized ground slope) (?o) being at least equal to a predetermined ground slope (?i).

Abstract: According to the invention, the engine pylon for the suspension of a turbo engine under an aircraft wing is such that the trailing edge of the rear lower part of the engine pylon is shifted toward the root of the wing.