Thales

Liebherr-aerospace Toulouse Sas

Joël Bosson

Marc Etienne Fumey

Sylvain Lissajoux

Eric Ravindranath Dubois

Hocine Kherbouchi

Tarik Aegerter

Christophe Garnavault

Eric Guillouet

Jean-Christophe Reculeau

Vincent Gomez

Frederick Clement

Patrick Cadotte

Yves Meyer

Hubert Lacquit

The protection of an electrical energy accumulation device from electromagnetic attacks is provided. The electrical energy accumulation device comprises a housing made of an electrically conductive material, at least one electrical energy storage cell that is arranged in the housing and two terminals that are arranged through the housing, the terminals being electrically insulated from the housing, the terminals allowing electrical energy to be transferred between the at least one storage cell and the exterior of the device. The device further comprises, inside the housing, a specific component exhibiting an impedance having at least one resistive component that is higher than 1 ohm, which component is configured to dissipate the energy of electromagnetic interference attempting to penetrate the housing through at least one of the terminals.

Protection of an electrical energy accumulation device

This method for installing avionics software applications on a platform with a multi-core processor and intended to be on board an aircraft is implemented by an electronic installation device. Each avionics software application includes one or several software processing operations to be executed over a predefined time period including one or several successive time clusters. It comprises determining an installation plan for the software processing operations according to a first installation rule and/or a second installation rule, the installation plan defining, for each software processing operation, at least one core and at least one time cluster that are associated with said software processing operation, the first rule consisting of predetermining a list of authorized combinations of criticality levels for applications intended to be executed during a same time cluster, and the second rule consisting of prohibiting installation of critical software application(s) on one or several cores of the plurality of cores.

Method and electronic device for installing avionics software applications on a platform comprising a multi-core processor, related computer program and electronic system

A programmable electronic computer embedded in an avionics environment on board an aircraft for implementing at least one critical function and associated electronic device, method and computer program are disclosed. In one aspect, the electronic computer includes at least one control module configured to implement a respective critical function and configured to deliver at least one output data item associated with the critical function, and at least one monitoring module of a control module of another electronic computer. Each monitoring module configured to implement the same respective critical function as the one implemented by the monitored control module.

Programmable electronic computer in an avionics environment for implementing at least one critical function and associated electronic device, method and computer program

This method makes it possible to generate a resulting setpoint trajectory of an aircraft, a guiding system controlling the trajectory of the aircraft relative to the resulting setpoint trajectory. The generating method is implemented by an electronic device and comprises selecting at least one mode from among several operating modes, acquiring a setpoint trajectory prepared by a flight management system, obtaining an alternative setpoint trajectory from an element from among a module for computing a trajectory and an external generating system, and generating the resulting setpoint trajectory, which includes one or several segments of the alternative setpoint trajectory for the period of time corresponding to the selection of another mode.

Method and device for generating a resulting setpoint trajectory of an aircraft, related computer program product and aircraft

Energy management on board an aircraft includes: a plurality of thermal and electrical energy sources, a plurality of loads which are capable of being supplied with power by the various energy sources, among which at least one load is capable of being supplied with power by an electrical energy source and by a thermal energy source, and real-time management means for energy transfers from the various energy sources to the various loads as a function of the present and future energy requirement of the various loads and the present and future availability of the various sources, with the management means providing a permanent and standardized correlation between thermal and electrical energies.

Energy management on board an aircraft

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Chatou, France

Joël Bosson