Airbus Operations (s.a.s.)

Airbus France

Airbus Corporation

Airbus Operations Gmbh

Fabrice Villaume

Pierre Scacchi

David Chabe

Robert Lignee

Armand Jacob

Jean Duprez

Eric Godard

Christophe Jourdan

Dominique Chatrenet

Vincent Blondin

Fabien Lavergne

Jérôme Journade

Mikaël Maas

Celine Bourissou

Louis-Emmanuel Romana

Mikael Maas

Method and device for assisting in the piloting of an aircraft during a landing. The device () contains means () for calculating turnaround times depending on the use of thrust reversers upon landing, as well as means () to display these turnaround times.

Method and device for assisting in the piloting of an aircraft during a landing

A method and device automatically controls the driving of an aircraft along a ground path of an airport domain. A guidance system is configured to determine, with the aid of at least one current value of the aircraft and a ground rolling trajectory, a yaw rate setpoint enabling the aircraft to follow the ground rolling trajectory by application of a yaw rate command. The guidance system, with the aid of measured current values of parameters of the aircraft, the determined ground rolling trajectory and a speed profile that incorporates a variation of the longitudinal speed along the ground trajectory, a longitudinal speed setpoint that represents a longitudinal speed command to drive the aircraft along the ground trajectory, while complying with the speed profile. A piloting aid system calculates setpoints from the yaw rate command and applies the setpoints to control yaw motion of the aircraft.

Method and device concerning the taxiing of an aircraft, which is automatic at least in part

Disclosed is a method and device for aiding the piloting on an aircraft during a landing phase. One of the landing runways of an airport onto which the aircraft is to land is determined by a runway determination device. A position determining unit is used to determine a current position of the aircraft in a reference frame. A minimum breaking distance is estimated by an estimation unit, upon the aircraft passing above tje determined landing runway. The minimum braking distance is compared by a distance comparison unit with a length of the determined landing runway, and an alert is emitted by an alert unit, when said minimum braking distance is greater than the length of said determined landing runway.

Method and device for aiding the piloting of an aircraft during a landing

Disclosed is a method and system for managing a convoy of aircraft during taxiing. Taxi management is carried out by exchanging, by a first data transmission unit, information between the aircraft of the convoy concerning aircraft flight parameters of the aircraft within the convoy, and exchanging, between the aircraft of the convoy and at least one control station that manages the convoy collectively, information relating to the collective convoy. The exchange can be carried out by a second data transmission unit, with the ground control station receiving from each aircraft in the convoy information relating to convoy status, centralizing the received information, scheduling the convoy, and transmitting to each aircraft a convoy status table that indicates overall status of the convoy.

Method and system for automatically managing a convoy of aircraft during a taxiing

Disclosed is a method and device for generating a yaw rate command for an aircraft along a ground trajectory. The yaw rate command is generated by determining a current curvature, lateral deviation and angular deviation of the ground trajectory. A yaw rate calculator then calculates a yaw rate and generates the yaw rate command based on the determined current curvature, lateral deviation and angular deviation.

Method and device for generating a yaw speed order for an aircraft during a taxiing

A method and device to assist in the piloting of an aircraft in a landing phase may apply a maximum braking of the aircraft if there is a risk of longitudinal departure from a runway.

Method and device to assist in the piloting of an aircraft in a landing phase

Disclosed is a system for generating a controlled speed for an aircraft along a ground trajectory. The system provides for receiving a ground trajectory of the aircraft and the speed profile of the aircraft. An interpolated speed of the aircraft is calculated on the basis of the ground trajectory, the speed profile and the current position; a weighting factor is calculated from an angular deviation, which is calculated from a measured current aircraft heading and the ground trajectory; an auxiliary speed is determined from the calculated interpolated speed; and the determined auxiliary speed is multiplied by the weighting factor to generate the controlled speed.

Method and device for generating a speed for an aircraft during a taxiing

Disclosed is a method and device for generating an aircraft ground path for piloting an aircraft along the ground of an airport domain. Geographical coordinates of reference points corresponding to a series of elements of the airport domain that the aircraft is to successively follow are obtained and converted to a metric frame. Points of intersection of the successive elements are then determined, as well as an auxiliary path for the aircraft to follow, based on the converted geographical coordinates. A turn at each of the intersection points is next determined, and the aircraft ground path is generated from each of the determined turns.

Method and device for generating a taxiing trajectory for an aircraft

A method and device for generating a speed profile for an aircraft rolling on the ground. The device () comprises means () for automatically determining a speed profile which is suited to successive elements of a ground rolling trajectory and which complies with maximum speeds and particular constraints.

Method and device for generating a speed profile for an aircraft during a taxiing

The device () comprises means () for calculating a controlled speed enabling the aircraft to observe a longitudinal separation relative to an aircraft of the convoy that precedes it.

Method and device for generating a taxiing speed for an aircraft of a convoy

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

A device has a pitch acceleration instruction calculator that calculates a pitch acceleration instruction depending on a pitch objective and a deflection instruction calculator that calculates, from the pitch acceleration instruction, a deflection instruction for elevators of an aircraft.

Active pitch control method and device for an aircraft

Automatic take-off method and device for an airplane. The device includes a device for automatically determining, using an elevation guidance objective, a vertical piloting objective which is expressed as rate of pitch, and a device for automatically determining, using the vertical piloting objective, deflection commands for elevators of the airplane.

Automatic take-off method and device for an airplane

The invention relates to an electric flight control system for aircraft elevators. According to the invention, the flight control system can be controlled in terms of load factor or rate of pitch. The inventive system comprises built-in protections in relation to load factor, incidence and pitch attitude.

Electric flight control system for aircraft elevators

The system includes a plurality of engines that generate a thrust of an aircraft, each of the engines controlled by a first controllable actuator. A plurality of brakes reduce the speed of the aircraft when it is taxiing, each of the brakes controlled by a second controllable actuator. A control unit generates a piloting setpoint that relates to the longitudinal behavior of the aircraft. A central processing unit automatically determines, from the piloting setpoint, a plurality of individual control commands that are applied automatically to the first and second actuators and used to satisfy the piloting setpoint and a usage objective for the actuators.

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Seysses, France

Fabrice Villaume