Airbus Operations (s.a.s.)

Airbus France

Airbus Operations Gmbh

Stéphane Delannoy

Jean Muller

Fabrice Villaume

David Chabe

José Torralba

Thierry Bertin

A system for controlling aircraft flight control surfaces implements a method including: obtaining a control law for the flight control surfaces as a function of flight controls of the aircraft; obtaining measurements of ground speed, true speed, roll angle, pitch angle, angle of attack, sideslip angle and slope angle; performing an estimation of the wind in three dimensions using the measurements obtained; performing an adjustment of the control law for the flight control surfaces, to counter the estimated wind effect and to obtain an adjusted control law for the flight control surfaces, by adding, to the control law, a term for wind compensation comprising a term proportional to the derivative of the wind estimation; and controlling the aircraft by applying the adjusted control law. Thus, the impact of the wind on the aircraft is reduced by digital processing and automatic adjustment of the control of the flight control surfaces.

Method for adjusting aircraft controls

A system including a set of computation modules configured to be utilized for computation of gains of at least one piloting law relative to at least one piloting axis of the aircraft and a data capture unit for capturing in at least one computation unit associated with a given piloting axis of the aircraft first values illustrating aerodynamic coefficients of the aircraft and second values defining delay and filter characteristics of the control chain relative to the given piloting axis, the computation unit being configured to compute the gains of the piloting law utilizing at least a part of the set of computation modules and the computation unit computing inputs intended for at least one actuator of a control surface adapted to control the aircraft relative to the given piloting axis in accordance with a corresponding current control value.

Aircraft flight control method and system

A method and device for displaying trim information on an airplane during a take-off, for determining and displaying a precise trim setpoint which enables the pilot, by following the displayed information, to carry out a manual take-off which is optimized from the performance point of view.

Method and device for displaying trim information on an airplane during a take-off

The flight-control device () makes it possible, by offsetting part of a flight command according to a particular flight path, to obtain the same control as is obtained with usual flight control, but without flexible excitation that generates discomfort in the aircraft.

Method and device for piloting an aircraft about a piloting axis

The device for flying an aircraft includes a first unit for determining a control value corresponding to an instruction value representing the actuation of a control member by a pilot, a second unit for determining an effective control value corresponding to the instruction value which is actually applied to the aircraft, a third unit for automatically controlling the aircraft, a fourth unit for computing an auxiliary control value, which is closer to the effective controlled value, and a fifth unit for monitoring the control value and for detecting a pilot induced oscillation, where the automatic control is carried out with the aid of the controlled effective value and the auxiliary control value in the case of the detection of the pilot induced oscillation.

Method and device for flying an aircraft according to at least one flying line

A control device a determination device for determining a roll objective, and a calculation device for calculating, on the basis of the roll objective, a deflection order which is applied exclusively to ailerons of the aircraft.

Method and device for active control of the roll of an aircraft

The invention relates to a method and device for piloting a pitching aircraft. The inventive device () comprises: means () for receiving an ordered load factor (NZc); means () for estimating a load factor (NZcg) that is applied to the aircraft; a means () for calculating a control order for a means () for deflecting a control surface () of the aircraft, taking account of at least the following expression K1&#xb7;NZc+K2&#xb7;NZcg, K1 and K2 representing gain values; means () for determining the Mach number; means () for determining the angle of incidence; means () for comparing the angle of incidence with a reference value; and means () for determining a modified gain value (&#x394;K2) with the aid of the Mach number and the angle of incidence if said angle of incidence is greater than the reference value, said modified gain value (&#x394;K2) replacing gain value K2 in the calculation performed by the calculation means ().

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Pujaudran, France

Stéphane Delannoy