Airbus France

Airbus Operations (s.a.s.)

Gérard Mathieu

Franck Delaplace

Sylvie Marquier

Gennaro Squeglia

Rémi Bellouard

Benoît Lemaignan

Nicolas Daniel

A method and device control the thrust of a multi-engine aircraft. At least one engine command is determined by a command determining unit, with the determined command commanding each engine that has not failed to deliver a thrust substantially equal to a reduced thrust value. A command application unit is configured to apply the determined command to each aircraft engine that has not failed. The reduced thrust value is determined, by a weight determining device, according to the current weight of the aircraft and according to a reduced thrust value FOEI, which is calculated by a thrust calculation unit.

Method and device for controlling the thrust of a multi-engine aircraft

Detection of the overstepping of design loads of an aircraft tailplane may include determining current bending and twisting moments applied to the aircraft. The determined bending and twisting moments are compared with a safety envelope to determine the risk of developing permanent deformations on the tailplane. A determination is made as to whether a structural inspection of the tailplane should be performed based on the comparison result.

Method and device for detecting an overstepping of design loads of the tailplane of an aircraft

An aircraft takeoff process may include applying a pitch command deflecting an adjustable horizontal tailplane of the aircraft by a predetermined angle. Thereafter, the pitch command is corrected in accordance with the deviation between a takeoff rotation speed and a stall reference speed VRref of the aircraft.

Process for aiding the takeoff of an aircraft

A method and device for detecting an overstepping of design loads of the fin of an aircraft. The device includes a set of information sources and a section for determining, with the aid of information emanating from the set of information sources, a current bending moment. The device further includes a section for determining, with the aid of information emanating from the set of information sources, a current twisting moment, and a section for carrying out a comparison by comparing the pair formed by the current bending moment and the current twisting moment with a safety envelope representing a chart formed in a plane on the basis of pairs of values of bending and twisting moments and defined so that, for any pair which lies outside the safety envelope, there exists a risk of appearance of permanent deformation on the fin. The device further includes a section for determining whether a structural inspection of the fin has to be performed, at least on the basis of a comparison result provided by the comparison section.

Method and device for detecting an overstepping of design loads of the fin of an aircraft

Method and device for controlling and braking an aircraft running on the ground According to the invention, the aircraft () comprises two close undercarriage wheel assemblies (D,G) and two distant undercarriage wheel assemblies (D,G), the biggest of the braking commands (FD, FG) can, under certain conditions, be applied not only to the corresponding two undercarriage wheel assemblies, but also to the close undercarriage wheel assembly corresponding to the smallest braking command.

Method and device for controlling and braking an aircraft running on the ground

A process and device for detecting on an aircraft an overshoot of design loads at the level of a structural part of the aircraft. The detection device includes a speed measuring device for measuring an effective speed of the aircraft. A first comparator compares the measured effective speed with a maximum speed relating to the current flight configuration of the aircraft. A vertical load measuring device measures a vertical load factor of the aircraft, and a second comparator compares the measured vertical load factor with a limit value of the vertical load factor. An inspection determining device determines whether a structural inspection needs to be performed at the level of the structural part, based of the results of the first and second comparisons.

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Pibrac, France

Gérard Mathieu