Airbus Operations (s.a.s.)

Airbus Corporation

Dcns

Naval Group

Airbus Operations Gmbh

Xavier Dal Santo

Paule Botargues

Pascale Louise

Thierry Bourret

Jean Muller

Pierre Fabre

Xavier Guery

Olivier Sapin

Vincent Bompart

Armand Jacob

Malika Essadouni

Emmanuel Cortet

Alain Dupre

Nicolas Cellier

Alexandre Colomer

Sofien Kerkeni

Anthony Atencia

Céline Drouet

Disclosed is a method and a device for improving the safety of a maritime platform, installed at sea or navigating at sea, including an observation of sea waves striking the maritime platform, an operation of the maritime platform being controlled via a control system. The method and device are suitable for: &#x2014;acquiring elevation values of the surface of the sea at a plurality of points, making it possible to characterize at least one group of sea waves, a sea wave being likened to a wave defined by a period and an amplitude, &#x2014;calculating at least one characteristic quantity of each group of waves, &#x2014;comparing the calculated characteristic quantity to a hazard threshold, &#x2014;if the comparison indicates the hazard threshold is crossed, raising an alert intended for the control system.

Method and device for improving maritime platform safety

This naval platform () of the type including at least one hull () equipped with steerable thrusters () distributed on the latter and means () for controlling the orientation and the actuation of the latter, is characterized in that the control means comprise means () for illustrating at least one portion of the surface of the water around the naval platform () in proximity to the latter, associated with the means () for controlling at least one portion of the steerable thrusters () for generating and directing a waterflow towards this portion of the surface.

Naval platform provided with at least one hull comprising steerable thrusters

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

The invention relates to a method for controlling the deceleration on the ground of a vehicle. The method obtains, from the crew of the vehicle or from an outside operator, parameters relating to its current position and its current speed. Then it determines a reference position and speed of the vehicle, the reference position being a theoretical position to be reached by the vehicle. Finally it determines, from indicated parameters and from reference parameters, a deceleration command with a view to ending up at a target position at a preselected speed.

Method for controlling the deceleration on the ground of a vehicle

The guiding mode transition aiding device includes a target heading determining device and a mode transition triggering system. The target heading determining device is configured to determine a target heading which represents the heading value reached by the aircraft at the end of a procedure of folding the wings of the aircraft flat from a current operating state. The mode transition triggering system receives the target heading and compares the target heading to a desired heading to be reached by the airplane to assist with triggering a transition between a rolling angle holding mode, in which the aircraft flies with a constant rolling angle, to a heading holding mode, in which the aircraft flies with a constant heading. This device and associated methods may be used during in flight refueling operations.

Method and device for aiding the control of guiding modes transitions of an aircraft

A method of aiding the piloting of an airplane ensures the availability of an automatic pilot and a thrust regulation system on board the airplane. To this end, the method includes determining first information by measuring the actual airspeed of the airplane, and this first information is used to control the automatic pilot and the thrust regulation system in a primary mode during normal operations of the airplane. When the first information is lost by becoming unavailable or unreliable, the automatic pilot and the thrust regulation system are each controlled in a secondary mode by control parameters determined using additional flight data independent from the actual airspeed of the airplane and the first information. Consequently, an alternative or redundant control is supplied for ensuring the continued operation of an automatic pilot without necessary intervention from crew members on board the airplane.

A method and device for assisting in driving a vehicle in motion along an initial trajectory, in an environment containing at least one obstacle, assistance is carried out by checking, by a trajectory checking unit, during movement of the vehicle, the existence of at least one condition for modifying the initial trajectory to avoid the obstacle. A criteria determining unit is used to determine a criterion CR by which to avoid the obstacle, and an avoidance trajectory determining unit is used to determine an avoidance trajectory according to a derivative of the criterion CR. The vehicle is assisted along the determined avoidance trajectory by a driving assist device.

Method and device to assist in the driving of a vehicle, in particular of an aircraft, for the avoidance of obstacles

According to the invention, the device () comprises means () for detecting, during an altitude capture maneuver, the emission of a first type alarm by the anti-collision system () and means () for controlling the vertical speed of said airplane (AC), after the emission of such an alarm, until the triggering of the capture phase.

Method and device for preventing an anti-collision system on board an airplane from emitting alarms, during an altitude capture maneuver

According to the invention, the device () comprises means () for adapting the altitude capture maneuver, means () for first detecting the emission of a first type alarm, means () for determining a first alarm threshold and means () for establishing an activation height threshold from said first alarm threshold and airplane vertical speed at the time of the alarm emission, so that, when the height separating said aircraft (AC) from the altitude set level is strictly higher than said height threshold at the time of the alarm emission, said adaptation means () are disabled.

Disclosed are a method and device for attenuating vertical turbulence encountered by an aircraft during flight. Incorporated into the method and device is a wind determination device, which is used to determine a vertical wind component existing outside the aircraft. A severity level determination unit is used to determine a severity level of the vertical wind component determined by the wind determination device. A control unit calculates at least one control order based on the vertical wind component determined by the wind determination device. In addition, the control unit determines the actual existence of activation conditions determined according to the severity level determined by the severity level determination unit. Upon verifying the activation conditions, the control unit transmits the control order to at least one actuator of the at least one controllable movable member.

Method and device for attenuating on an aircraft the effects of a vertical turbulence

The invention relates to a method and device for limiting the number of alarms generated by an anticollision system on board an airplane according to which the duration of a phase of capture of a setpoint altitude by the airplane is adjusted so that a theoretical time for collision with an intruder aircraft is greater than a predetermined threshold, when the airplane is close to said setpoint altitude and air traffic exists in the environment of said airplane.

Method and device for limiting the number of alarms generated by an anti-collision system on board an airplane

The invention describes a method and device for preventing useless alarms generated by an anticollision system on board an airplane and according to which the duration (dcap) of a phase of capture of a setpoint altitude (Zc) by the airplane is between a predetermined minimum execution deadline (dmin) and a predetermined maximum execution deadline (dmax).

Method and device for preventing useless alarms generated by an anti-collision system on board an airplane

Disclosed is a method and device for automatically protecting an aircraft against a hard landing. A measuring unit measures current vertical speed and current relative height of the aircraft. A first command generating unit generates first commands to act on the vertical speed of the aircraft by determining an intermediate command from the measured vertical speed and height and converting the intermediate command into turn angles. A speed calculation unit applies the first commands to control surfaces. The first commands are generated from the measured current vertical speed and height, taking into account a predetermined reference vertical speed, such that the aircraft touches down on the ground at a vertical speed not greater than the predetermined reference vertical speed.

Growing community of inventors

Blagnac, France

Xavier Dal Santo