Abstract: A system to communicate via modulated optical signals of the Li-Fi signal type to transmit data to and from a plurality of defined privileged spaces. The communicating system includes a plurality of first light sources, each first light source emitting, in the infrared, a first modulated optical signal. A plurality of optical fibers, each optical fiber guiding the first modulated optical signal from a single first light source in the direction of an optical interface. The optical interface transmitting the first modulated optical signal into a defined privileged space. Each optical fiber also transporting a second modulated optical signal from the associated defined privileged space in the direction of a device configured to acquire the second modulated optical signal.

Abstract: A data management structure (1a) on board a transportation device, incorporating a cabin (100) provided with seats (110), includes a data resource block (210) incorporating audiovisual transmission system units (211 to 213), outward communication systems (100) and/or cabin systems, a standardised data distribution architecture (10a), and devices (E1 to E4) for operating said systems. In the structure (1a), the standardised architecture (10a) includes a concentration box (11) for the bidirectional transfer, on the one hand, of base signals with the resource block (210) and, on the other hand, optical signals with the devices (E1 to E4) of the cabin (100) on at least one optical fibre (2, 3; 2a, 2?a; 2b). This concentration box (11) houses units for processing (211 to 213) by signal switching, bidirectional conversion into optical signals, and optical signal management by wavelength allocation and distribution of downstream (F1) and upstream (F2) optical flows.

Abstract: The invention relates to the on-board electric power network architecture of a vehicle cabin using domestic devices, in particular of an aircraft cabin, including primary networks (11, 12) connected in parallel to a single domestic network (3) of the cabin for powering domestic devices via converter units (41, 42; 40). Measurement sensors (80) are arranged at the output of each converter unit (41, 42; 40) and the measurements are transmitted (L1) to a regulating device (9) for sharing the supply of the domestic network (3) according to the available power, each converter unit (41, 42; 40) comprises an upstream processing stage (E1) and a downstream processing stage (E2), each including an anti-disturbance device (D1, D2), linked (B1, B2) with the primary network (11, 12) and linked (B3, B4) with the domestic network (3), respectively.

Abstract: A system to communicate via modulated optical signals of the Li-Fi signal type to transmit data to and from a plurality of defined privileged spaces. The communicating system includes a plurality of first light sources, each first light source emitting, in the infrared, a first modulated optical signal. A plurality of optical fibers, each optical fiber guiding the first modulated optical signal from a single first light source in the direction of an optical interface. The optical interface transmitting the first modulated optical signal into a defined privileged space. Each optical fiber also transporting a second modulated optical signal from the associated defined privileged space in the direction of a device configured to acquire the second modulated optical signal.

Abstract: A data management structure (1a) on board a transportation device, incorporating a cabin (100) provided with seats (110), includes a data resource block (210) incorporating audiovisual transmission system units (211 to 213), outward communication systems (100) and/or cabin systems, a standardised data distribution architecture (10a), and devices (E1 to E4) for operating said systems. In the structure (1a), the standardised architecture (10a) includes a concentration box (11) for the bidirectional transfer, on the one hand, of base signals with the resource block (210) and, on the other hand, optical signals with the devices (E1 to E4) of the cabin (100) on at least one optical fibre (2, 3; 2a, 2?a; 2b). This concentration box (11) houses units for processing (211 to 213) by signal switching, bidirectional conversion into optical signals, and optical signal management by wavelength allocation and distribution of downstream (F1) and upstream (F2) optical flows.

Abstract: The invention relates to the on-board electric power network architecture of a vehicle cabin using domestic devices, in particular of an aircraft cabin, including primary networks (11, 12) connected in parallel to a single domestic network (3) of the cabin for powering domestic devices via converter units (41, 42; 40). Measurement sensors (80) are arranged at the output of each converter unit (41, 42; 40) and the measurements are transmitted (L1) to a regulating device (9) for sharing the supply of the domestic network (3) according to the available power, each converter unit (41, 42; 40) comprises an upstream processing stage (E1) and a downstream processing stage (E2), each including an anti-disturbance device (D1, D2), linked (B1, B2) with the primary network (11, 12) and linked (B3, B4) with the domestic network (3), respectively.

Abstract: An electrical power supply device for an aircraft on the ground, the device including two electricity generators driven by an auxiliary power unit, wherein the first generator is connected by a selective connection/disconnection mechanism to an aircraft network and to an electrical taxiing network, and is configured to deliver either a first AC voltage to the aircraft network when it is connected to that network, or an AC voltage or a power to the taxiing network when it is connected to that network, and wherein the second generator is connected by the connection/disconnection mechanism to the aircraft network to deliver the first AC voltage to that network solely when the first generator is powering the taxiing network.

Abstract: An aircraft including an electric starter-generator for each of turbojets, and an undercarriage including an electric motor for taxiing the aircraft, which mutualizes an electricity converter for starting and for taxiing the aircraft. A single electricity converter is configured to be coupled to the electric starter-generator associated with a turbojet or to the electric motor of the undercarriage for taxiing, the coupling take place via an electricity distribution unit.

Abstract: An electrical power supply device for an aircraft on the ground, the device including two electricity generators driven by an auxiliary power unit, wherein the first generator is connected by a selective connection/disconnection mechanism to an aircraft network and to an electrical taxiing network, and is configured to deliver either a first AC voltage to the aircraft network when it is connected to that network, or an AC voltage or a power to the taxiing network when it is connected to that network, and wherein the second generator is connected by the connection/disconnection mechanism to the aircraft network to deliver the first AC voltage to that network solely when the first generator is powering the taxiing network.

Abstract: An aircraft including an electric starter-generator for each of turbojets, and an undercarriage including an electric motor for taxiing the aircraft, which mutualizes an electricity converter for starting and for taxiing the aircraft. A single electricity converter is configured to be coupled to the electric starter-generator associated with a turbojet or to the electric motor of the undercarriage for taxiing, the coupling take place via an electricity distribution unit.

Abstract: A starter/generator mechanically coupled to a gas turbine transmission housing is disclosed. The starter/generator includes a generator with a rotor forming a field winding and a stator forming an armature, and an energizer with a stator forming a field winding and a rotor forming an armature connected to the generator field winding. The generator rotor and the energizer rotor are mounted on a common shaft with a transmission housing gear wheel, on either side of the gear wheel.

Abstract: A starter/generator mechanically coupled to a gas turbine transmission housing comprises a generator (10) with a rotor forming a field winding and a stator forming an armature, and an energizer (20) with a stator forming a field winding and a rotor forming an armature linked to the field winding of the generator. The rotor (12) of the generator and the rotor (22) of the energizer are mounted on a common shaft (54) together with a gear (86) of the transmission housing, one on each side of this gear.

Abstract: An arrangement for electrically powering an aircraft comprises at least one first generator driven by an engine of the aircraft, an electricity network on board the aircraft receiving the voltage produced by the first generator, at least one second generator driven by the motor, and an engine electrical network distinct from the on-board network for powering equipment of the engine of its environment, the engine network comprising: at least one DC electrical voltage distribution bus for the electrical equipment; and a power supply circuit having a first input connected to the on-board network, a second input connected to the second generator to receive the electrical voltage supplied thereby, a voltage converter connected to the second input, and a selector circuit for delivering a voltage on the distribution bus, the voltage being supplied from that received on the first input or from that supplied by the converter depending on the amplitude of the voltage supplied by the second electricity generator.

Abstract: A system for powering and controlling electrical equipment of an aircraft engine or of its environment, includes at least one DC voltage power supply bus, a set of power supply modules associated with an electrical equipment group, each module including a voltage converter and a selector circuit inserted between the outputs from the modules of the set of modules and the pieces of equipment of the equipment group. The modules and the selector circuit are controlled to activate each piece of equipment of the equipment group by connecting it to at least one of the modules, with an emergency module being put into operation in the event of one of the other modules failing.

Abstract: A main generator delivers an AC voltage to an electricity network on board an aircraft via a main line having at least one line contactor mounted therein, the voltage being regulated by a regulator. An engine electricity network delivers electricity to various loads situated in the zone of an engine fitted to the aircraft and to an engine control computer, the engine electricity network having a first fed input connected to the main electricity power supply line via a secondary electricity power supply line, upstream from the line contactor in order to receive directly electricity derived from the main generator without transiting via the electricity network on board the aircraft. The voltage regulator regulating the voltage delivered by the main generator may be situated in the engine zone and is powered by the engine electricity network.

Abstract: A system for powering and controlling electrical equipment of an aircraft engine or of its environment, comprises at least one DC voltage power supply bus, a set of power supply modules associated with an electrical equipment group, the number of modules in the set being greater than the minimum number needed for activating the electrical equipment of the group in such a manner as to provide at least one emergency module, each module comprising a voltage converter to supply at the output of the module an alternating voltage derived from the DC voltage of the power supply bus, and a selector circuit inserted between the outputs from the modules of the set of modules and the pieces of equipment of the equipment group. The modules and the selector circuit are controlled to activate each piece of equipment of the equipment group by connecting it to at least one of the modules, with an emergency module being put into operation in the event of one of the other modules failing.

Abstract: An arrangement for electrically powering an aircraft comprises at least one first generator driven by an engine of the aircraft, an electricity network on board the aircraft receiving the voltage produced by the first generator, at least one second generator driven by the motor, and an engine electrical network distinct from the on-board network for powering equipment of the engine of its environment, the engine network comprising: at least one DC electrical voltage distribution bus for the electrical equipment; and a power supply circuit having a first input connected to the on-board network, a second input connected to the second generator to receive the electrical voltage supplied thereby, a voltage converter connected to the second input, and a selector circuit for delivering a voltage on the distribution bus, the voltage being supplied from that received on the first input or from that supplied by the converter depending on the amplitude of the voltage supplied by the second electricity generator.