Airbus France

Airbus Operations (s.a.s.)

Franck Delaplace

Gérard Mathieu

Sylvie Marquier

Gennaro Squeglia

Dieter Lang

Jean Muller

Gerard Mathieu

Frédéric Sauvinet

Didier Ronceray

Xavier Le Tron

Sophie Lambeaux

Martin Richter

Dominique Buisson

Nicolas Daniel

Frederic Sauvinet

According to the invention, high lift leading-edge slats () and high lift flaps () are simultaneously deployed, when the speed of the aircraft is equal to and less than an AES threshold.

Method for piloting an aircraft in approach phase

An energy protecting device for three and four-engined aircraft includes a detecting unit configured to detect failure of each engine. A control unit is configured to provide a protective function by controlling maximum thrust of each engine. A triggering unit is configured to monitor a plurality of parameters and trigger the control unit to provide maximum thrust at predetermined conditions of the monitored parameters. An inhibiting unit is linked to the triggering unit and is configured to inhibit the protective function, when at least one of the engine on the wings of the aircraft has failed. The control unit is also configured to control the engines that have not failed to minimize thrust imbalance.

Energy protecting device for aircraft

In conformance with the invention, based on the incident conditions and velocity, the steering of the ailerons is weakly negative (b) or corresponds either to the maximum sharpness of the aircraft (b), or the optimal lift of the latter (b).

Method and device for piloting an aircraft optimizing the control of the ailerons in an enhanced-lift configuration

A reference value is arbitrarily selected from a range of possible aircraft rotation speeds. A position of a trimmable horizontal stabilizer is angled in accordance with a centering of the reference value. A deviation between the reference value and an accelerating speed value of the aircraft is determined. Elevators or the horizontal stabilizer are controlled, prior to rotation, in accordance with the determined deviation.

Assisted take-off method for aircraft

The invention relates to a method and device for reducing the wake vortices of an aircraft during the approach/landing phase. Spoilers are automatically ordered to deploy when lift-augmenting aerodynamic surfaces are ordered to deploy, and are automatically ordered to retract when at least one of the following three conditions holds: the angle of incidence &#x3b1; of the aircraft is equal to or greater than an incidence threshold &#x3b1;s; the speed Vc of the aircraft is equal to or less than a speed threshold Vs; and the aircraft is instigating a go-around maneuver.

Method and device for reducing the wake vortices of an aircraft in the approach/landing phase

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

A control system for an aircraft includes an actuation section that moves lift-enhancing devices as a function of received control orders, a control member operable by a pilot of the aircraft, and a control unit that includes a control section that produces control orders, as a function of actuation of the control member, so as to control the actuation section to bring the lift-enhancing devices into a predetermined position. The control unit further includes a device that produces automatically auxiliary control orders which are transmitted to the actuation section to automatically retract the lift-enhancing devices when the aircraft is in a first flight condition and another device that automatically disables control orders produced by the control section following actuation of the control member to deploy the lift-enhancing devices when the aircraft is in a second flight condition.

System for automatically controlling lift-enhancing devices of an aircraft, in particular wing leading edge slats

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

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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Toulouse, France

Franck Delaplace