Airbus Operations (s.a.s.)

Airbus Operations Gmbh

Marc Fervel

Antoine Maussion

Arnaud Lecanu

Jean-Jacques Aubert

Alexandre Gentilhomme

Philippe Goupil

Patrice Brot

Jean-Louis Lando

Alain Guillet

Laurent Andrieu

Sylvain Sauvant

Gilles Tatham

Ina Ruckes

Tobias Sebastian Rumpf

A flight control system for an aircraft comprises a set of actuators for controlling the aircraft and a set of flight control computers only made up of a set of duplex type main computers and of at least one backup computer. All the main computers are configured to implement auto-pilot laws for the aircraft. The set of main computers comprises two computers from a first hardware type, configured to control actuators of the set of actuators as per a first tolerance level and two computers from a second hardware type, different from the first hardware type, configured to control actuators of the set of actuators as per a second tolerance level, less stringent than the first tolerance level.

Flight control system for an aircraft

The invention relates to an aircraft control system, situated in the avionics bay, including a computer, a remote equipment, such as an actuator of control surfaces, and an AFDX network. The computer includes a first module and a second module, respectively connected to a corresponding first module and a second module of the equipment, by a first and a second virtual link sharing a common path through the network, the first and second virtual links being segregated by a separate encoding at the applicative level. A replication and/or frame switching device is connected, on the one hand, to the common port and, on the other hand, to the ports of the first and second modules of the equipment.

Aircraft control system with merged links

A device for making available navigation parameter values of a vehicle is provided. The device includes components distributed in the following categories: several sensors collecting measurement data relating to at least one navigation parameter of the vehicle; several computers processing the measurement data collected by the sensors and calculating said navigation parameters; several networks linking the sensors to the computers and linking the computers to systems using said parameters. The networks transmit all the collected measurement data to the computers, which calculate a value for each navigation parameter as well as an estimated value of the associated fault, using a single common fusion algorithm.

Device for making available navigation parameter values of a vehicle

A flight control system for an aircraft, intended for controlling a plurality of actuators adapted for actuating control surfaces of the aircraft from information supplied by piloting members and/or sensors of the aircraft. The system includes a primary control system adapted for controlling a first set of control surface actuators and a secondary control system adapted for controlling a second set of control surface actuators, the primary and secondary systems being respectively powered by independent energy sources of different types.

Distributed flight control system implemented according to an integrated modular avionics architecture

The present invention discloses a method for controlling a high-lift device or a flight control surface of an aircraft or spacecraft, especially with a system according to the present invention, comprising the steps of receiving, at least one first control unit, a command signal from a commander unit via a data network, providing a primary control signal to at least one secondary control unit via the data network, wherein the primary control signal depends on the received command signal, receiving, at the at least one second control unit, a sensor signal of one or more sensors of the high-lift device or flight control surface, and providing a secondary control signal to one or more actuators of the high-lift device or flight control surface, wherein the secondary control signal depends on the received sensor signal. Furthermore, the present invention discloses a system and an aircraft or spacecraft.

Method for controlling a high-lift device or a flight control surface, system and aircraft or spacecraft

An electric flight control system onboard an aircraft provided with flight control surfaces and controllers for controlling these surfaces, that include at least one local electro-hydraulic generator to supply hydraulic servocontrols connected to flight control surfaces.

More electric flight control system onboard an aircraft

An aircraft control system in which a plurality of elementary control systems, corresponding to different aircraft functions, can share one or more sensors due to a common AFDX network. The transmission of commands is carried out via AFDX messages sent to network-subscribed actuators. Advantageously, the computers of the different elementary control systems installed in the avionics bay include generic computers hosting software specific to execution of respective functions thereof (IMA architecture).

Aircraft control system with integrated modular architecture

A flight control system for an aircraft, controlling a plurality of actuators adapted to actuate control surfaces of the aircraft, including: at least one communications bus; at least one computer situated in the avionics bay of the aircraft, and adapted to calculate flight commands and to transmit them over the bus in the form of command messages; and at least a first remote terminal connected to the bus, adapted to control a control surface actuator, and to acquire the state of the actuator from information provided by at least a first sensor, the first terminal receiving command messages from the computer and transmitting electrical orders to the actuator as a function of the command messages received in this way, and also transmitting messages to the computer, at its request, relating to the state of the actuator as a function of the information provided by the first sensor.

Distributed flight control system

The invention relates to a flight control system for an aircraft comprising control surfaces and actuators associated with the control surfaces to control flight functions, including roll, yaw, pitching, and aerodynamic braking of the aircraft. The actuators associated with the control surfaces that control at least one of the flight control functions are electromechanical actuators. A part of the control surfaces associated with the electromechanical actuators is divided, where each of the divided control surfaces is comprised of at least two independent surfaces.

Power takeoff means () for this flight control system adjacent to the aircraft engines () are all-electric and this makes it possible to reduce the length of hydraulic connections leading to actuators of the controlled devices (). Electrical generators are of different types to minimize the risk of a generic failure. Characteristically of the invention, some generators () have a constant voltage to frequency ratio and directly or almost directly control electro-hydraulic pumps (), without modifying the current characteristic and with no power electronics. Furthermore, system reconfigurations are made possible by additional electrical connections () in case of failure.

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Toulouse, France

Marc Fervel