Airbus Operations (s.a.s.)

General Electric Company

Airbus (Sas)

Airbus Operations Sl

Aerospatiale Societe Nationale Industrielle

Airbus France

Societe Nationale Industrielle Et Aerospatiale

Airbus Operations Gmbh

Airbus Corporation

Patrick Zaccaria

Robert Charles Hon

Tod Robert Steen

Laurent Saint-Marc

Michael Scott McCambridge

Didier Poirier

Carlos Casado-Montero

Pio Fernandez-Lopez

Philippe Chareyre

Julien Feau

Amid Ansari

Thomas Earl Gillingham

Panxika Larramendy

Paul-Emile Roux

Daniel Roy Kiracofe

Kenneth Kirchmayer

Alexis Manneville

Guillaume Alix

Thierry Immordino

Jean-François Belkadi

David Boyer

Patrice Ostermann

Emmanuele Costanzo

Thierry Clavel

Laurent Bouin

Luc Brunel

Matthieu Alexandre

Frédéric Leborgne

Christine Molliet

Francedillaois Garavel

Nathalie Durand

Pierre-Henri Brousse

Pierre Daste

Laurent Saint Marc

Marie-Pierre Fuertes

Damien Lozach

Souhaib Boukayoua

Lucie Coue

Sébastien Tranchard

Frederic Leborgne

Francois Garavel

To control an engine shutdown in an aircraft, a control system includes a fuel supply shut-off member, a control member with a set of switches, a first switch on an electrical power supply link of the fuel supply shut-off member and second switches connected to avionics of the aircraft, the set of switches switching position on an engine shutdown command. An engine shutdown confirmation unit includes a third switch on the electrical power supply link, the third switch in open position by default. The engine shutdown confirmation unit includes electronic circuitry configured to switch the third switch over to closed position when a predefined quantity Q of switches of the control member switches position within a sliding window of predefined duration and, otherwise, keeps the third switch in open position. Thus, it is ensured that the engine shutdown is intentional.

System for confirming shutdown of an aircraft engine

A system and a method for the automatic starting of the engines of a twin-engine aircraft. When a first engine is made by the pilots of the aircraft to follow an automatic starting procedure, this engine follows the conventional four-phase starting cycle. The rotor of the high-pressure stage of the second engine is spun up for a predetermined duration and to a speed that is substantially constant and less than the nominal value during the starting cycle for the first engine. Once the starting cycle for the first engine is complete, the second engine is made by the pilots of the aircraft to follow an automatic starting procedure. The starting cycle for the second engine comprises just three phases.

System and method for starting the engines of a twin-engine aircraft

A start-up system including a control system controlling a partial opening of an air intake valve of a start-up turbine during a first phase of the start-up. The start-up turbine is capable of turning a rotor of the turbomachine for the purpose of the start-up, so as to prevent the rotor from encountering critical frequencies of the turbomachine.

Method and system for starting up an aircraft turbomachine

The start-up system comprises a control loop, which regulates in real time the opening of a valve of an air feed of a start-up turbine based on the current measured speed of rotation of a rotor of the turbomachine and a predetermined speed value, said start-up turbine being capable of turning the rotor of the turbomachine for the purpose of the start-up.

Method and system for starting up an aircraft turbomachine by real-time regulation of air flow

An aircraft comprising at least two engines and an electronic management arrangement comprising a control computer for each engine, each computer being configured for monitoring the operation of its associated engine and for activating an engine protection mode when the engine operation exceeds predetermined operational limits. The electronic management arrangement furthermore comprises an engine interface device to which the control computers are connected, the device prohibiting the activation of a protection mode by a control computer when a protection mode is activated by another control computer. A monitoring device is connected to the control computers and receives an information signal from each control computer to indicate if a protection mode is activated and transmits, in the case where a protection mode is activated on at least two engines, a control signal to the control computer having last activated a protection mode to cancel the activation of the protection mode.

Aircraft equipped with a device for monitoring the electronic management of the engines

A monitoring system and a monitoring method applied to the monitoring system, in which the monitoring system includes detectors detecting a state of a turbojet thrust reverser, a monitoring computer device controlling the reverser monitored by the computer as a function of information from the detectors provided to the computer by way of the control device, and a device regulating the turbojet monitored by the computer as a function of the information from the detectors provided to the computer by way of the control device.

Control and monitoring system and method

A device for a motorized aircraft includes at least one avionic component positioned in the aircraft, at least one engine interface positioned in the aircraft and at least one engine controller positioned in or near an engine of the aircraft. The at least one engine interface is designed to exchange data between the at least one avionic component and the at least one engine controller. The at least one engine interface is generic and able to communicate with engine controllers of various types that may be mounted on the aircraft. The at least one engine controller is specific to a particular engine.

FADEC and avionic component distributed architecture

A device for issuing authorization to act on the operating conditions of an aircraft engine and engine control system includes a first unit for determining particular parameters concerning the aircraft, including the position of a power lever controlling the supply of fuel to the engine, and a second unit for determining, based on the particular parameters, whether the aircraft is in a state authorizing an action on the operating conditions of the engine and for issuing, as the case may be, a corresponding authorization signal.

Device for issuing authorization to act on the operating conditions of an aircraft engine and engine control system comprising same

An engine control system for a first aircraft belonging to a family of aircraft which includes at least a second aircraft, the first aircraft having a maximum mass which is greater, within a predetermined limit, than that of the second aircraft. For an engine of the first aircraft, a first thrust command law controls a thrust of an engine of the first aircraft during take-off phase (T), and a second thrust command law, controls a thrust of the engine to correspond with a part of the thrust command laws applicable to the second aircraft during all other flight phases (R) of the first aircraft. The transition from one flight phase to another is detected to supply the engine with a control signal corresponding to one or the other of the first thrust command law or the second thrust command law.

Engine control system for an aircraft

The present invention relates to a device for controlling the thrust of an aircraft, with several engines (M1, M4), comprising calculation units (UC1, UC4) that formulate first commands for controlling the engine speeds. According to the invention, said device (1) additionally comprises means (CONT1, CONT4) of controlling the two outer engines (M1, M4), calculation means that formulate second commands for controlling the speed of the outer engines (M1, M4) making it possible to obtain a reduction in thrust, and switching means which, during normal operation of the outer engines (M1, M4) send the first commands to these engines and, when one outer engine (M1) fails, send the second commands to the opposite outer engine (M4).

Device for controlling the thrust of a multi-engine aircraft

Growing community of inventors

Toulouse, France

Patrick Zaccaria