Airbus Operations (s.a.s.)

Airbus (sas)

Jerôme Bazile

Patrice Rouquette

Matthias Eberle

Sylvain Raynaud

Nicolas Marconnet

Philippe Perrin

Mathieu Reguerre

Guillaume Discours

Kevin Etchebarne

Fabrice Butin

The system for aiding the landing of an aircraft on a landing runway of an airport equipped with an Instrument Landing System ('ILS') corresponding to an axis of a predetermined approach, includes: an ILS signals receiver and a processing unit. The processing unit is configured to, when the ILS signals receiver) has not yet captured a Glide signal corresponding to a Glide axis of the approach as a function of items of information relating to the predetermined approach, acquired from a database, determine a protection volume in which there is no risk of the ILS signals receiver detecting a replica of the Glide signal; and when a current position of the aircraft is above the protection volume, inhibit the capture of the Glide signal by the ILS signals receiver and instruct the emission of an alert item of information in the cockpit of the aircraft.

System and method for aiding the landing of an aircraft

A device for managing configurations of an aircraft between an initial point and a final point comprises a computation module to determine at least one first evolution curve considering the aircraft to have assumed a first configuration and wherein the first evolution curve includes the first point and a final evolution curve considering the aircraft to have assumed at least one final configuration and wherein the final evolution curve or curves includes the final point, a computation module to compute at least one second point corresponding to the intersection of the first evolution curve or curves and the final evolution curve or curves, and a transmission module configured to transmit a signal representing the coordinates of the second point or points to a user device.

Aircraft configuration management method and device

A device including an acquisition module for acquiring current parameters of the aircraft, a computational module for computing a current load factor of the aircraft, a computational module for computing a minimum load factor, a computational module for computing the difference between the current load factor and the minimum load factor, and an acoustic emission module for emitting a sound signal, the level of which increases gradually as a function of time when the difference between the current load factor and the minimum load factor is less than zero.

Method and device for assisting with the landing of an aircraft during a flare maneuver

A method and device for assisting initiation of a flare maneuver of an aircraft during a landing. The device includes an acquisition unit for acquiring current values of flight parameters of the aircraft, including the current height of the aircraft with respect to the ground, a computation unit for computing a first reference height and a second reference height, corresponding to a height starting from which the aircraft attains a current start of flare height while maintaining its current descent conditions over a predetermined first duration and over a predetermined second duration respectively, and an acoustic emission unit for emitting at least two sound signals in the cockpit of the aircraft, namely a first sound signal when the current height of the aircraft attains the first reference height during the descent and a second sound signal when the current height of the aircraft attains the second reference height during descent.

Method and device for assisting the intiation of a flare maneuver of an aircraft during a landing of the aircraft

A method of determining a dynamic stability margin Mof an aircraft includes calculating the longitudinal position Xof a maneuver point MP to find the distance between the maneuver point and the position Xof the aircraft center of gravity CG, as a function of the angular velocity &#x3c9;of an incidence oscillation of the aircraft. A device for determining the dynamic stability margin Mor a position Xof the maneuver point MP includes means or acquisition of data and or calculating a dynamic stability margin. The means receive data for generating, the aircraft mass m and pitch inertia Iyy; the flight speed V; the angular velocity &#x3c9;of the incidence oscillation at a flight point; a coefficient C*representing Czof a 'quasi-static' model of the aircraft. The aircraft flight control laws may be adapted according to the stability margin and to X.

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Leguevin, France

Jerôme Bazile