Airbus Operations (s.a.s.)

Sylvain Raynaud

Jean-Claude Mere

Patrice Rouquette

Jean-Damien Perrie

Florent Lanterna

Martin Legay

Arnaud Nicolas

Simon Sellem

Jean Muller

Jean-Pierre Demortier

Jean-Louis De Menorval

Christophe Bouchet

Maxime Wachenheim

Thomas Pastre

Marc Vie

Esteban Quiroz-Hernandez

Fabien Perrin

Nicolas Potagnik

Jerôme Bazile

Nicolas Marconnet

Jean Guilhamet

Jean-Christophe Guillermin

Daniel Zapata-Arenas

François Cusset

Guillaume Discours

Alexandre Grattard

Kevin Etchebarne

Jérôme Bazile

An aircraft with a unit to transmit information on ability/inability of pilots to fly the aircraft. Guidance avionics include guidance architecture and a flight controller to fly the aircraft. The guidance architecture has two dissimilar guidance chains and a selection unit connected thereto, to the flight controller and to the unit for measuring physical ability/inability, a first guidance chain to compute a main path for the aircraft towards a destination airport based on a current state of the aircraft by following a flight plan and to compute main guidance instructions for following the main path, a second guidance chain to compute an emergency path for the aircraft towards a diversion airport based on an initial portion of the common path with the main path and to compute emergency guidance instructions for following the emergency path. The selection unit receives the main and emergency guidance instructions and transmits either one to the flight controller.

Aircraft comprising a flight management architecture

A flight management assembly of an aircraft and method of monitoring the flight management assembly. The assembly includes two flight management systems, and a monitoring and backup unit, each of the flight management systems configured for generating data including a trajectory and a prediction of a parameter of the aircraft, one of the flight management systems being active and the other being passive, the monitoring and backup unit configured for carrying out monitoring of at least one of the items of data generated by the active flight management system in order to verify if the item of data is valid, the flight management assembly carrying out, in case of validation of the monitored item of data, a synchronization of the monitoring and backup unit and of the passive flight management system, with data called synchronization data of the active flight management system, namely a flight plan and/or a flight trajectory.

Flight management assembly of an aircraft, of a transport aircraft in particular, and to a method of monitoring such a flight management assembly

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 method and device for adjusting performance variables of an aircraft. The device which is intended for adjusting performance variables, the performance variables being generated by at least one performance module, includes an auxiliary data input unit for entering into a flight management system correction data intended to be used for adjusting at least one associated performance variable, and a correction unit for carrying out a correction, the correction including adjusting the associated performance variable on the basis of the input correction data.

Method and device for adjusting performance variables of an aircraft

The invention relates to a flight management assembly () comprising two guidance chains (A,B), each one provided with a flight management system (A,B), each of said flight management systems (A,B) carrying out at least one calculation of guidance instructions for the aircraft, the flight management assembly () also comprising at least one monitoring unit (A,B) designed to monitor the guidance instructions calculated by the two flight management systems (A,B) in such a way as to be able to detect and identify a defective flight management system, the monitoring unit (A,B) comprising a monitoring device () which verifies particularly whether the following three conditions are met: a first derivative of extrapolated cross tracks is positive; a second derivative of extrapolated cross tracks is positive; and extrapolated positions of the aircraft are on the same side of an active segment of the flight plan followed by the aircraft as the current position of the aircraft.

Assembly for the flight management of an aircraft and method for monitoring guidance instructions for such an assembly

A flight management unit includes two guidance subsystems each including a flight management system, each of the flight management systems being configured at least to extract a flight plan from at least one navigation database, to construct a flight trajectory, and to compute guidance commands for the aircraft. The flight management unit also includes at least one monitoring unit configured to compute a guidance command from a validated flight trajectory and a consolidated flight plan and to monitor the guidance command, as well as guidance commands computed by the two flight management systems so as to be able to detect and to identify a defective flight management system.

Aircraft flight management unit and method of monitoring such a unit

A method and device for aiding piloting of an aircraft during an approach phase for the purpose of landing. The device includes a guidance system for guiding the aircraft according to a first guidance mode during an initial phase upstream of a transition point, then guiding the aircraft according to a second guidance mode during a terminal phase between the transition point and the landing, the device further including a computing system for automatically computing the coordinates of the transition point, the guidance system also configured for automatically disabling the second guidance mode upstream of the transition point.

Method and a device for aiding piloting of an aircraft during an approach phase for landing

The device aids the management of air operations, such as operations under Required Navigation Performance with Authorization Required maneuvers. The device includes a guidance system including a plurality of stages for calculating parameters, each of the stages including an architecture having at least three pieces of equipment, which calculate the parameters and implement monitorings to determine the status of the equipment. The device uses these monitored statuses to determine a global status that indicates if the aircraft is able to carry out the air operations with required performance.

Method and device for aiding the managing of air operations with required navigation and guidance performance

A method is disclosed for automatic monitoring of a flight management assembly of an aircraft implementing air operations necessitating guaranteed navigation and guidance performance, wherein flight path data generated by first and second flight management systems respectively, are compared in order to check their consistency; first and second flight management systems transmit their flight path data to a third flight management system; the third flight management system receives a current position of the aircraft, calculates deviations between this current position and a flight path depending on the flight path data received from the first and second flight management systems, which it utilizes only if they are identical, and calculates, according to these deviations, guidance commands for slaving onto this flight path. Monitoring can compare deviations and guidance commands received from the first second and third flight management systems in order to be able to detect an inconsistency between them.

Method for the automatic monitoring of air operations necessitating guaranteed navigation and guidance performance

The system () comprises means for determining the distance at the current time of the target aircraft (B) with respect to the merge waypoint (P0) along its path (TB), this distance being transmitted to calculation means in order to determine the speed control commands which are subsequently applied to the reference aircraft (A) in order for it to carry out the acquisition of the spacing at said merge waypoint (P0).

Method and device for automatically managing the spacing of at least one following aircraft behind at least one target aircraft

A monitoring device includes one or more devices for implementing monitoring, in order to check whether two flight management systems are able to operate in dual mode during operations requiring navigation and guidance performance. For example, a change condition verification device may be included in a second or slave flight management system so that sequencing requests and resynchronization requests received from a first or master flight management system are verified for accuracy before implementation. The verification may include comparison of positional data used by the first and second flight management systems or a comparison of a resynchronized flight plan to information from a navigation data database.

Method and device for automatically monitoring air operations requiring navigation and guidance performance

Disclosed is a method and device of guiding an aircraft along a flight trajectory to comply with a time constraint for arriving at a required arrival time at a waypoint of the flight trajectory. Speed setpoints are determined according to a speed profile that complies with the required arrival time at the waypoint, based on estimated values of parameters relating to the flight of the aircraft, and by taking account of an upper limit for a maximum speed at which the aircraft flies along the flight trajectory. The determined speed setpoints are applied to the aircraft during guidance of the aircraft along the flight trajectory.

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Cornebarrieu, France

Sylvain Raynaud