Abstract: A generation method performed by a generator module of an electricity network of an aircraft, the electricity network including a power supply line powered by the generator module, a DC bus powered from the power supply line via a rectifier, and at least one electrical actuator powered with AC from the DC bus via an inverter. The generation method includes: delivering an AC voltage as a function of a voltage setpoint and of a voltage measured in the on-board network; and determining the voltage setpoint as a function of an operating parameter of the actuator.

Abstract: A power supply circuit for supplying electrical energy in an aircraft, the circuit including a power supply generator configured to be driven in rotation by the engine of the aircraft to power electrical equipment of the aircraft engine. The power supply generator includes an asynchronous machine connected to an excitation device. The asynchronous machine includes a rotor configured to be driven in rotation by the engine and a stator connected to the electrical equipment. The excitation device is configured to cause a reactive current of flow in the stator.

Abstract: An electric brake system for an electromechanical machine connected to output terminals of an inverter, input terminals of which are supplied by a DC voltage source. The system includes an electrical circuit connected between the input terminals of the inverter and including, connected in series: a mechanism dissipating electrical energy returned by the electromechanical machine to the input terminals of the inverter during a braking phase of the electromechanical machine, including an inductor wound around a magnetic circuit; and a switching mechanism to close the electrical circuit during a braking phase of the electromechanical machine and to open the electrical circuit in absence of a braking phase of the electromechanical machine.

Abstract: An aircraft engine including: a stator; a main shaft; a first rotor; a second rotor; a transmission mechanism; a first electrical apparatus supported by the first rotor and a second electrical apparatus supported by the second rotor; at least one first field winding supported by the stator; a control unit configured to circulate direct electric current in the first field winding; at least one first armature winding supported by the first rotor and connected to the first electrical apparatus and at least one second armature winding supported by the second rotor and connected to the second electrical apparatus.

Abstract: An apparatus including a fixed part, a rotary support configured to be driven in rotation relative to the fixed part, at least one item of electrical equipment carried by the rotary support, and a power supply device configured to supply electrical energy to the electrical equipment. The power supply device includes an asynchronous machine including a stator fixed to the fixed part and a rotor carried by the rotary support, and an excitation device. The stator includes an electrical circuit including at least one switch configured to switch between an open state in which the electrical circuit is open and a closed state in which the electrical circuit is closed. The rotor includes at least one winding connected to the electrical equipment. The excitation device is configured to provide a reactive current to the electrical circuit of the stator or to the winding of the rotor.

Abstract: An actuator device for actuating a swivel-mounted member carried by a rotor of a propulsion engine including: at least one electricity source; an electric actuator for swiveling the swivel-mounted member; a power supply circuit connecting the electricity source to the actuator; and an inertial device connected to the power supply circuit, the inertial device configured to convert electrical energy coming from the power supply circuit into mechanical energy, to store the mechanical energy, and to convert the mechanical energy into electrical energy for the power supply circuit.

Abstract: A polyphase electrical machine controlled by at least two parallel inverters, each including a number of branches equal to a number of phases of the machine and controlled by PWM. When detecting an inverter branch is faulty, the faulty branch is isolated and the phase in question is powered by each corresponding other inverter branch. The PWM is modified to make power switches of each other branch conductive in succession, without switching while absolute value of the current of the phase in question is greater than or equal to a threshold of 80% to 120% of (n?1)Imax/n, n is number of inverters and Imax is maximum magnitude of the phase current. It is thus possible to continue generating substantially sinusoidal voltages on each of the phases, while avoiding overdimensioning the power switches to ensure in event of a fault they can deliver currents of amplitude higher than in normal operation.

Abstract: A turbine engine starter-generator including a main electrical machine including a stator and rotor with a wound rotor inducer and damper bars forming a cage, and an exciter including a stator inducer and rotor with rotor windings connected to the rotor inducer of the main electrical machine via a rotary rectifier. During a first starting stage, the electrical machine operates in asynchronous motor mode by injecting AC into its stator windings, a starting torque being generated by the damper bars, without the rotor inducer of the main electrical machine contributing significantly to generating starting torque. Then in a second starting stage, the main electrical machine operates in synchronous motor mode by injecting AC into its stator windings, while feeding its rotor inducer with DC via the exciter, the change from the first stage to the second stage taking place when rotation speed of the shaft reaches a predetermined value.

Abstract: An electrical system (18, 20, 22) for starting an engine, the system comprising: an AC/DC rectifier (12) powered by an AC power network (14) to deliver a first DC voltage Vdc, and a DC/AC converter module (16) for delivering an AC voltage for starting the engine from said first DC voltage Vdc, the system comprising k n-phase inverters arranged in parallel (k>1) and each delivering power no greater than half a maximum power Pmax required for starting the engine, and the two power supply lines of each of the inverters are connected to an electronic protection device receiving the first DC voltage Vdc, and the n outputs of each of the inverters delivering the AC voltage for starting the engine via n respective series inductors.

Abstract: An electric brake system for an electromechanical machine connected to output terminals of an inverter, input terminals of which are supplied by a DC voltage source. The system includes an electrical circuit connected between the input terminals of the inverter and including, connected in series: a mechanism dissipating electrical energy returned by the electromechanical machine to the input terminals of the inverter during a braking phase of the electromechanical machine, including an inductor wound around a magnetic circuit; and a switching mechanism to close the electrical circuit during a braking phase of the electromechanical machine and to open the electrical circuit in absence of a braking phase of the electromechanical machine.

Abstract: A device for cooling electrical or electronic equipment in a turbomachine, such as a unit for controlling actuators for variable-geometry elements, the device comprising at least one vortex tube having an inlet connected to means for feeding pressurized air taken from an element of the turbomachine, and a cold air outlet connected to means for cooling the electrical equipment.