Airbus France

Airbus Operations (s.a.s.)

Airbus Operations Gmbh

Christophe Bouchet

Jean-Pierre Demortier

Franck Artini

Sylvain Raynaud

Maxime Wachenheim

Marc Vie

Edward Strongman

Esteban Quiroz-Hernandez

Jacques Espinasse

François Barre

Romain Merat

Jeremy Berard

Alexandre Lanoix

Emmanuel Blanvillain

François Cusset

Pierre Daste

Alexandre Grattard

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 vertical profile management device includes a flight management system unit that selects a plurality of successive standard cruise sections, each comprising a level phase and a transition phase. The cruise sections are defined by a plurality of features, including waypoints corresponding to a section starting point and a section ending point, a transition type, a transition mode, a transition speed, a level altitude, and a level speed. The flight management system unit also joins together the successive cruise sections in order to form a vertical profile of a flight plan. The cruise sections are configured to be added, removed, or re-sequenced in the flight plan because each section ending point is configured to be the section starting point of a next cruise section in the series.

Method and device for automatically managing the vertical profile of the flight plan of an aircraft

Disclosed is a method and device for guiding an aircraft flying along a flight trajectory. The flight trajectory has at least one constrained section, and the aircraft flies at a required speed within the constrained section to comply with a required arrival time at a predetermined waypoint in the constrained section. Auxiliary speed setpoints are determined to guide the aircraft to arrive at an auxiliary arrival tune at an auxiliary waypoint, with the auxiliary speed setpoints being applied by a guidance system to guide the aircraft.

Method and device for guiding an aircraft

An aircraft terrain avoidance system include a device having a first unit knowing a profile of the terrain that is located at the front of the aircraft, a second unit for determining an avoidance trajectory, a third unit which is connected to the first and second units and used to verify if there is a terrain collision risk for the aircraft, a fourth unit for emitting an alarm signal in the event of detection of a collision risk by the third unit, at least one aircraft performance database relating to an avoidance maneuvering gradient which can be flown by the aircraft according to particular flight parameters, and a fifth unit for determining the effective values of the particular parameters during the flight of the aircraft. The third unit is formed such that it is possible to determine the avoidance trajectory according to information received from the database and the fifth unit.

Aircraft terrain avoidance and alarm method and device

A system determines a limit angle of climb corresponding to a climb angle of an aircraft for flying over the ground along an avoidance path and displays a characteristic sign representing the limit angle of climb on a display screen.

Method and system for assisting flight control of a low-flying aircraft

A device for constructing and securing a low altitude flight path intended to be followed by an aircraft. The device includes a first processing unit which has a Design Assurance Level (DAL) C requirement level and which determines a low altitude flight path, using data coming from a first database qualified according to a Data Process Assurance Level (DPAL) 2 standard, and a second processing unit which has a DAL A requirement level and which checks the flight path determined by said first processing unit, using data corning from a second database qualified according to a DPAL1 standard.

Device for constructing and securing a low altitude flight plan path intended to be followed by an aircraft

Method and device for ensuring the safety of a low-altitude flight of an aircraft. A device () for ensuring the safety of a low-altitude flight comprises information sources () able to determine current flight conditions, a monitoring unit () for realizing, with the aid of said current flight conditions, a function for global and autonomous monitoring of said low-altitude flight of the aircraft, making it possible to preserve the integrity of said aircraft during said flight, and means () for presenting the results of the monitoring function realized by said monitoring unit () to an operator.

Method and device for ensuring the safety of a low-altitude flight of an aircraft

A flight control indicator for an aircraft has a set of information sources, a computation unit which determines, on the basis of information emanating from the set of information sources, an item of information regarding actual thrust of an engine of the aircraft, and a display device which is a head-up display device and which presents, on a display screen, an indication of the item of information regarding actual thrust. The item of information regarding actual thrust is associated with a thrust scale and both are presented superimposed on the environment prevailing in front of the aircraft.

Flight control indicator displaying the aircraft's thrust information

A flight control indicator for an aircraft includes a central unit that determines a change of vertical or lateral trajectory. A display, which may present a first indicator of a next vertical change and a second indicator of a next lateral change, presents the one of the first and second indicators indicating the change of trajectory which is closest from the current position of the aircraft.

Flight control indicator for an aircraft

A method and device for calculating a target speed of an aircraft may include a flight point time determining section that determines when the aircraft actually gets to a particular flight point, taking account of the aircraft's current target speed. A time interval calculating section calculates a time interval between the predetermined time at which the aircraft must get to the particular flight point and the determined actual time. A speed updating section updates the target speed and applies the updated target speed to the aircraft if the calculated time interval is greater than a duration of comparison, which is variable and depends on the actual distance so as to decrease when the actual distance decreases.

Method and device for calculating a target speed for an aircraft

The flight control indicator may include a set of information sources, a computation unit connected to said set of information sources, and a head-up display device. The computation unit determines, on the basis of information emanating from the set of information sources, at least one maximum total slope of the aircraft. The maximum total slope corresponds to the maximum thrust and is obtained on the basis of the measurement of the current performance of the aircraft, extrapolated to the condition of maximum slope and in anticipation of an engine fault. The head-up display device presents, on a display screen, at least one indicator which indicates the maximum total slope and which is presented superimposed on the environment existing in front of the aircraft.

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Toulouse, France

Christophe Bouchet