Airbus Operations (s.a.s.)

Airbus France

Airbus (Sas)

Airbus Operations Gmbh

Thierry Bourret

Jean Muller

Pascale Louise

Florent Lanterna

Nicolas Chauveau

Claire Ollagnon

Xavier Dal Santo

Guillaume Alcalay

Sebastien S Giuliano

Kenji Ahualle Horimoto

Pierre Scacchi

Paule Botargues

Jean-Damien Perrie

Matthieu Mayolle

Nicolas Potagnik

Olivier Sapin

Nicolas Marconnet

Alain Tanguy

Erwin Grandperret

Cécile Puissacq

Matthieu Barba

Franck Laine

Imad Lebbos

Pascale Louise-Babando

Maxime Semat

Lucas Burel

Vincent Lautridou

Sébastien Drieux

Matthieu Boitrel

Charles Renault Lerberquer

Laurent Goutal

Stéphane Granger

Michel Padovani

Sabrina Betton

Mathieu Galy

Pierre-Antoine Lierman

Marie-Odile Plantecoste

Didier Sauve

Stephane Granger

A method and system for determining a position error of an aircraft. The system comprises a set of collection modules implemented in an iterative manner, including an offset collection module, a position vector collection module, a set of sequentially implemented computation modules, including an angular alignment bias computation module, an observable position bias computation module and a position error computation module. The system thus allows a position error to be determined that is used to perform a landing in good conditions.

Method and system for determining a position error of an aircraft

A method and system for estimating an angular deviation from a reference guidance axis, a position and a velocity of an aircraft. The system includes an offset collection module for collecting an offset measured by a measurement module, a position vector collection module for collecting a position vector measured by a position vector measurement module, a velocity vector collection module, a module for estimating the angular deviation of a reference guidance axis with respect to the approach axis towards the runway, for estimating the position of the aircraft with respect to the runway and for estimating the velocity of the aircraft with respect to the runway.

Method and system for estimating an angular deviation from a reference guidance axis, a position and a velocity of an aircraft

A verification method comprising a first step of measuring at least one position parameter of an aircraft and a first set of steps implemented after the flight of at least one aircraft, in an automatic and repetitive manner, comprising computing a geographical height of an aircraft with respect to the runway on the basis of the position parameters of an aircraft, computing an evaluated vertical deviation, between the geographical height and a reference height, and computing a vertical error on the basis of a comparison between the evaluated vertical deviation and the reference vertical deviation.

Method and device for verifying a guidance signal

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.

Control system and method for an aircraft

A method and a system for controlling an emergency descent of an aircraft. The system () includes a unit () for detecting an emergency situation, a unit () for calculating a usual emergency descent command, a unit () for calculating a limited emergency descent command, a selection unit () configured for selecting the usual emergency descent command or, if application conditions are met and if the limited descent command is less than said usual emergency descent command and greater than a regulation emergency descent command, selecting the limited emergency descent command, and a unit () for application, to the aircraft, of the selected emergency descent command.

Method and system to control emergency descent of aircraft

An activation device comprising a computation unit configured to compute a stall margin of the aircraft, an information reception unit configured to receive information indicating if an automatic angle-of-attack protection system of the aircraft is active or inactive, and an activation unit configured to activate the display of the stall margin indicator only if the automatic angle-of-attack protection system is inactive.

Method and device for activating the display of at least one stall margin indicator of an aircraft

A method is described for aiding the piloting of an airplane by ensuring availability of an automatic pilot that is normally controlled as a function of speed information of the airplane when the speed information is lost. The method includes detecting a loss of the speed information of the airplane. In response to the detection of the loss of the speed information, the method includes determining flight data of the airplane being independent from the speed information of the airplane, determining control parameters from the flight data, and controlling the automatic pilot based on the control parameters and without the speed information of the airplane. The automatic pilot includes an automatic piloting system or a flight director.

Automatic method and device for aiding the piloting of an airplane

A method and device including a unit to extract a linear terrain profile stored in memory, a terrain height for a current distance of the aircraft, a unit for determining a current height of the aircraft with respect to the terrain, using at least one measurement taken by a radar altimeter, a unit for computing a first current altitude of the aircraft, using the terrain height and the current height, a unit for computing a second current altitude of the aircraft, corresponding to an altitude on an approach profile of the current position of the aircraft and a unit for computing the difference between the first and second current altitudes, the difference being transmitted to a guidance unit to vertically guide the aircraft.

Method and device for vertically guiding an aircraft during an approach of a runway along a lateral approach trajectory

A device comprising a computation unit for computing, for each of a plurality of different distances relative to a threshold of a landing runway along a lateral approach trajectory, a geometric altitude, using a measured and stored barometric altitude, a computation unit for computing a terrain height, by subtracting, from the computed geometric altitude, a measured and stored height, and a computation unit for determining a terrain profile from the set of terrain heights computed for the set of different distances.

Method and device for determining a linear terrain profile along a lateral approach trajectory of an airport

Methods, systems, and computer readable media are disclosed for direct arming aircraft runway approach guidance modes, for example and without limitation, for aircraft operational. In some aspects, a method for directly arming a runway approach guidance mode of an aircraft includes displaying on a display unit an airport, selecting the airport and selecting an active runway for final approach, displaying an path toward the selected final approach runway, selecting the final approach runway, displaying on the display unit at least one symbol associated with at least one runway approach guidance mode, and arming at least one of the at least one runway approach guidance mode.

Methods, systems and computer readable media for arming aircraft runway approach guidance modes

An automatic landing method and device for an aircraft on a runway with strong slope. The device includes means to automatically transmit, a runway slope value to an automatic piloting system of the aircraft, and said automatic piloting system uses the slope value to automatically manage the flare phase upon landing.

Automatic landing method and device for an aircraft on a strong slope runway

Interactive dialog device between an operator of an aircraft and a guidance system of the aircraft. The dialog device includes an interaction on a screen which represents, on the one hand, a playback element indicating the value of a guidance setpoint of the guidance system of the aircraft, and on the other hand, a control element which can be grasped and moved along a curve by an operator to modify the value of the guidance setpoint.

Interactive dialog device between an operator of an aircraft and a guidance system of said aircraft

Aircraft cockpit display screen with graphical user interface

A monitoring device for automatically monitoring the ability of an aircraft to follow a flight trajectory with at least one turn includes a series of elements that estimate the ability of the aircraft to follow at least one turn of the flight trajectory. For example, a turn radius and limit speed for each of the upcoming turns in a flight plan (or a partial portion of the upcoming turns) are analyzed by comparing to a current speed of the aircraft to determine if there will be any risk of excursion outside the flight plan path, such that warnings can be emitted to a crew of the aircraft to take corrective action before the turns are performed. Consequently, required navigational performance maneuvers can be assured before the beginning of the turns in the flight plan.

Method and device for automatically monitoring the ability of an aircraft to follow a flight trajectory with at least one turn

A method for automatically detecting an erroneous height value supplied by a radio altimeter mounted on an aircraft. The method includes measuring, during the aircraft's approach phase with a view to landing, the duration between the times when a first predetermined altitude threshold and a second predetermined altitude threshold are reached. This duration is measured by taking into account current height values supplied by the radio altimeter. The method then includes comparing the measured duration to a predetermined duration reference time, which is lower than a flight duration that would allow the aircraft to descend from the first predetermined altitude threshold to the second predetermined altitude threshold at a maximum vertical speed. An erroneous height value is detected if the measured duration is lower than the predetermined duration reference time.

Method and device for automatically determining an erroneous height value of a radioaltimeter mounted on an aircraft

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Toulouse, France

Thierry Bourret