Abstract: A DC/AC electrical power converter device having inlet terminals for electrically connecting to a DC electricity power supply network, outlet terminals for electrically connecting to an electric motor, a chopper electrical converter coupled to the inlet terminals, and an electrical inverter coupled between the chopper electrical converter and the outlet terminals. The converter device further includes a control unit for controlling the electrical inverter and that is configured to operate using pre-calculated pulse width modulation with pre-calculated unchanging switching instants for the controlled switches of the electrical inverter regardless of the frequency of rotation of the motor and of the voltage of the electricity network for connection to the device.

Abstract: A DC/AC electrical power converter device having inlet terminals for electrically connecting to a DC electricity power supply network, outlet terminals for electrically connecting to an electric motor, a chopper electrical converter coupled to the inlet terminals, and an electrical inverter coupled between the chopper electrical converter and the outlet terminals. The converter device further includes a control unit for controlling the electrical inverter and that is configured to operate using pre-calculated pulse width modulation with pre-calculated unchanging switching instants for the controlled switches of the electrical inverter regardless of the frequency of rotation of the motor and of the voltage of the electricity network for connection to the device.

Abstract: An electronic device with cooling of a heat dissipation source, by a liquid metals spreader, the device including at least one heat dissipation source, at least one spreader through which at least one liquid metal circulation channel passes forming a loop routed below a heat dissipation source, at least one heat sink, and at least one electromagnetic pump moving the liquid metal in the at least one channel such that the liquid metal absorbs heat dissipated by a heat dissipation source and transports the absorbed heat to be evacuated by the heat sink. Each spreader includes at least two plates made of an electrical insulating material located on each side of at least one bar made of deformable material.

Abstract: A method of controlling a permanent magnet synchronous machine including a stator and a rotor. The method includes determining an estimated position of the rotor, and determining a second in-phase voltage setpoint that, in alternation, is equal either to a first in-phase voltage setpoint or else to the first in-phase voltage setpoint plus a predetermined periodic signal. The determining an estimated position of the rotor includes determining a coupling term, determining a speed of rotation of the rotor as a function of the coupling term, and determining the estimated position of the rotor by integrating the speed of rotation of the rotor.

Abstract: A method of controlling a permanent magnet synchronous machine including a stator and a rotor. The method includes determining an estimated position of the rotor, and determining a second in-phase voltage setpoint that, in alternation, is equal either to a first in-phase voltage setpoint or else to the first in-phase voltage setpoint plus a predetermined periodic signal. The determining an estimated position of the rotor includes determining a coupling term, determining a speed of rotation of the rotor as a function of the coupling term, and determining the estimated position of the rotor by integrating the speed of rotation of the rotor.

Abstract: A device supplying electricity power to and actuating equipments of a gas turbine airplane engine, including an electricity power supply circuit dedicated to the engine and distinct from an electricity network on board the plane and excitation, control or servo circuits for pieces of electrical equipment of the engine. The engine electrical power supply circuit includes a first bus distributing DC or AC voltage to excitation, control or servo circuits for first pieces of electrical equipment of the engine, a second bus distributing DC or AC voltage to excitation, control or servo circuits for other pieces of electrical equipment of the engine requiring higher electrical power compared with the first pieces of equipment, and a third bus connected to receive power from an electricity source such as an airplane on-board electricity distribution network or an electricity generator dedicated to the engine and driven thereby. The third bus supplies the first and second bus with electricity power.

Abstract: A device supplying electricity power to and actuating equipments of a gas turbine airplane engine, including an electricity power supply circuit dedicated to the engine and distinct from an electricity network on board the plane and excitation, control or servo circuits for pieces of electrical equipment of the engine. The engine electrical power supply circuit includes a first bus distributing DC or AC voltage to excitation, control or servo circuits for first pieces of electrical equipment of the engine, a second bus distributing DC or AC voltage to excitation, control or servo circuits for other pieces of electrical equipment of the engine requiring higher electrical power compared with the first pieces of equipment, and a third bus connected to receive power from an electricity source such as an airplane on-board electricity distribution network or an electricity generator dedicated to the engine and driven thereby. The third bus supplies the first and second bus with electricity power.