Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: This method for implementing a partitioning during the execution of software applications on a platform comprising a multicore processor having several separate cores, is implemented by an electronic implementing device. It comprises a step for switching between the execution of a current set of software application(s) on a plurality of cores and the execution of a subsequent set of software application(s) on the plurality of cores, carried out in a synchronous manner on said plurality of cores, the step of synchronous multicore switching including one or more actions among a first group of actions consisting of: waiting, synchronized over the plurality of cores, for uninterruptible process(es) of the current set of software application(s) to finish running; and purging all memory resource(s) associated with the current set of software application(s).

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: The present invention relates to an aid system (30) for piloting an aircraft, the aircraft including at least two piloting units each having at least one piloting member that can be actuated by a pilot to command at least one control surface of the aircraft. The piloting aid system (30) includes a module (32) for detecting actions performed on at least one piloting unit and a feedback module (34) indicating, via a man-machine interface (24A, 24B) separate from the piloting members, the movement of said piloting member and/or the force exerted on said piloting member.

Abstract: 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.

Abstract: 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.

Abstract: The present invention relates to an aid system (30) for piloting an aircraft, the aircraft including at least two piloting units each having at least one piloting member that can be actuated by a pilot to command at least one control surface of the aircraft. The piloting aid system (30) includes a module (32) for detecting actions performed on at least one piloting unit and a feedback module (34) indicating, via a man-machine interface (24A, 24B) separate from the piloting members, the movement of said piloting member and/or the force exerted on said piloting member.

Abstract: 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.