Abstract: The invention concerns an aircraft comprising a reversible rotary electrical machine 30), a wheel (35) for imparting movement to a stream of air, linked to said machine (30), a first ventilation duct (10, 15) configured to supply said wheel (35) with air, an electricity distribution network (70), a reversible power converter (40) connected to said machine (30) and to said network (70), and a control circuit (50) configured to control said converter (40) for, in a motor operating mode of said machine (30), taking a supply current from said network (70) to supply said machine (30) and drive said wheel (35), and, in an alternator operating mode of said machine (30), in which a stream of air flows in said first ventilation duct (15) and imparts movement to said wheel (35), to provide supply power to said network (70) which is generated by said machine (30) driven by said wheel (35).

Abstract: The invention concerns an aircraft comprising a reversible rotary electrical machine 30), a wheel (35) for imparting movement to a stream of air, linked to said machine (30), a first ventilation duct (10, 15) configured to supply said wheel (35) with air, an electricity distribution network (70), a reversible power converter (40) connected to said machine (30) and to said network (70), and a control circuit (50) configured to control said converter (40) for, in a motor operating mode of said machine (30), taking a supply current from said network (70) to supply said machine (30) and drive said wheel (35), and, in an alternator operating mode of said machine (30), in which a stream of air flows in said first ventilation duct (15) and imparts movement to said wheel (35), to provide supply power to said network (70) which is generated by said machine (30) driven by said wheel (35).

Abstract: The invention relates to a system and a method for supplying power to an aircraft comprising several generators supplying alternating current to several different primary electrical master boxes (10, 11, 12 and 13), the various aircraft loads being connected to each of these master boxes. This system comprises conventional master boxes (10, 11, 12 and 13) which supply power loads and at least one master box (40, 41) devoted to actuator loads, this at least one devoted master box being connected to conventional master boxes.

Abstract: A combined device for instantaneous control of power transfer between two cores of a direct current network and for powering an alternating current engine. The device includes: an assembly of two three-phase inverters, each including three switching cells connected to the engine, which engine includes three stator windings connected to the two three-phase inverters, and a module for controlling the assembly, which ensures both an adjustable direct current power transfer and enables stabilization of the direct current voltage of one of the two cores if it is not connected, and the control of the engine.

Abstract: The invention relates to an electrical emergency source device fitted on an aircraft, which comprises an energy source capable of outputting the power necessary for vital electrical loads (10) to operate correctly, wherein there are two types of these loads: first loads, that absorb a constant power with time, second loads, that absorb variable power with time. Wherein this device comprises: a power source (12) sized to output the average power absorbed by all loads, a power source (15) capable of supplying power peaks absorbed by the second loads, and wherein, since the power of several loads is reversible, the power of the said device is also reversible.

Abstract: A device for controlling power transfer between two cores of a direct current network, in which the cores, which are source-charge interconnection nodes, include protective and contact members, placed in different areas of a power distribution system in which the direct current network is installed. The device includes an electronic power converter including two switching cells mutually interconnected by an inductance, wherein each switching cell includes two switches, and a module for controlling the converter, which ensures both a controllable direct current power transfer and stabilization of the direct current voltage.

Abstract: This invention relates to a device for supplying electrical power to an aircraft and for electrically starting a jet engine on board an aircraft, including a multi-phased starter-generator, a multi-phased transformer-rectifier unit, a multi-phased DC-AC converter, a multi-phased rectifier unit, and at least one three-phase inverter, wherein the number of phases is equal to or greater than 5.

Abstract: The invention relates to an electrical emergency source device fitted on an aircraft, which comprises an energy source capable of outputting the power necessary for vital electrical loads (10) to operate correctly, wherein there are two types of these loads: first loads, that absorb a constant power with time, second loads, that absorb variable power with time. Wherein this device comprises: a power source (12) sized to output the average power absorbed by all loads, a power source (15) capable of supplying power peaks absorbed by the second loads, and wherein, since the power of several loads is reversible, the power of the said device is also reversible.

Abstract: A device for controlling power transfer between two cores of a direct current network, in which the cores, which are source-charge interconnection nodes, include protective and contact members, placed in different areas of a power distribution system in which the direct current network is installed. The device includes an electronic power converter including two switching cells mutually interconnected by an inductance, wherein each switching cell includes two switches, and a module for controlling the converter, which ensures both a controllable direct current power transfer and stabilization of the direct current voltage.

Abstract: This invention relates to a device for supplying electrical power to an aircraft and for electrically starting a jet engine on board an aircraft, including a multi-phased starter-generator, a multi-phased transformer-rectifier unit, a multi-phased DC-AC converter, a multi-phased rectifier unit, and at least one three-phase inverter, wherein the number of phases is equal to or greater than 5.

Abstract: A combined device for instantaneous control of power transfer between two cores of a direct current network and for powering an alternating current engine. The device includes: an assembly of two three-phase inverters, each including three switching cells connected to the engine, which engine includes three stator windings connected to the two three-phase inverters, and a module for controlling the assembly, which ensures both an adjustable direct current power transfer and enables stabilization of the direct current voltage of one of the two cores if it is not connected, and the control of the engine.

Abstract: The invention relates to a system and a method for supplying power to an aircraft comprising several generators supplying alternating current to several different primary electrical master boxes (10, 11, 12 and 13), the various aircraft loads being connected to each of these master boxes. This system comprises conventional master boxes (10, 11, 12 and 13) which supply power loads and at least one master box (40, 41) devoted to actuator loads, this at least one devoted master box being connected to conventional master boxes.

Abstract: The invention concerns a method for controlling a static converter (1) associated with a polyphased electrical source (2) which consists in generating synchronizing times t(i) defined by a periodic clock T; measuring at least a value representing the state of the electrical source; computing from the measured values at least a control value {dot over (c)}(t) and its derivative c(t), and the value cp (t(i)+T) which each control value would have at the following synchronizing time t(i)+T, for the static converter configuration at time t(i); comparing each control value cp (t(i)+T) to a set value; determining said static converter configuration enabling to minimize the difference between each control value and the set value corresponding to the following synchronizing time t(i)+T; computing the derivative at time t(i)+T of a privileged control value, corresponding to the configuration Cc(t(i)+T) at time t(i)+T; determining the switching time t(i)+tcom between these times t