A fluid ice protection system for an aircraft includes a plenum back wall and a fluid delivery network. The plenum back wall is affixed to an interior surface of an inlet cowl of a nacelle of the aircraft to define a plenum between the interior surface and a front surface of the plenum back wall. The nacelle surrounds a rotor assembly of an aircraft propulsion system. The inlet cowl defines a plurality of perforations through a thickness of the inlet cowl. The perforations are fluidly connected to the plenum. The fluid delivery network is coupled to the plenum back wall and configured to supply an anti-ice liquid into the plenum for the anti-ice liquid to penetrate through the perforations onto an exterior surface of the inlet cowl along a leading edge section of the inlet cowl.

An example method of managing power in a hybrid propulsion system includes receiving, by one or more processors, a power demand that specifies an amount of power to be used to propel a vehicle that includes an electrical energy storage system (ESS) and one or more electrical generators, wherein the one or more electrical generators are configured to convert mechanical energy to electrical energy; determining, based on the power demand and a predetermined ESS output limit, a first amount of power to be sourced from the ESS and a second amount of power to be sourced from the one or more generators; and causing, by the one or more processors, the ESS to output the first amount of power onto a direct current (DC) electrical distribution bus and the one or more generators to output the second amount of power onto the DC electrical distribution bus.

An aircraft includes: rotors each driven by an electric motor; a PCU that converts AC power output from a generator into DC power; an inverter that converts DC power supplied from the PCU into AC power and outputs the AC power to the electric motor; a DC wire that connects the PCU and the inverter; and an AC wire that connects the inverter and the electric motor. The AC wire is disposed in a direction orthogonal to a direction in which rotation shafts of the generator and a gas turbine extend.

A rotary wing aircraft having an electrical installation including at least one thermopile for powering at least one piece of electrical load equipment. Technical specifications for the thermopile specify: a usable power for supplying to the load equipment in the range 20 W to 200 kW, a power rise time lapse lying in the range 3 s to 30 s, and a low operating time for usefully supplying a predetermined quantity of electrical energy lying in the range 10 s to 180 s. The invention applies in particular to rotary wing aircraft.

A DC-to-DC converter for an electrical aircraft propulsion system designed to be connected in series with an electrical energy storage unit of the electrical propulsion system. The DC-to-DC converter includes an inverter, a transformer and a rectifier, and further includes a current source that is connected to the rectifier and is configured to control the power passing through the DC-to-DC converter. The transformer includes a primary and two secondaries, the two secondaries sharing a common terminal designed to be connected to a high-voltage DC bus of the electrical propulsion system and two other terminals that are connected to the rectifier. The rectifier includes two arms including at least two transistors that are each in series and are connected, on the one hand, to the two other terminals of the transformer and, on the other hand, to the current source.

A DC-to-DC converter for an electrical aircraft propulsion system designed to be connected in series with an electrical energy storage unit of the electrical propulsion system. The DC-to-DC converter includes an inverter, a transformer and a rectifier, and further includes a current source that is connected to the rectifier and is configured to control the power passing through the DC-to-DC converter. The transformer includes a primary and two secondaries, the two secondaries sharing a common terminal designed to be connected to a high-voltage DC bus of the electrical propulsion system and two other terminals that are connected to the rectifier. The rectifier includes two arms including at least two transistors that are each in series and are connected, on the one hand, to the two other terminals of the transformer and, on the other hand, to the current source.

An assembly for an aircraft propulsion system includes a propulsor, an electric motor, and an electrical distribution system. The electric motor is operably connected to the propulsor and operable to drive rotation of the propulsor. The electrical distribution system includes an electrical power source, an electrical cable, and a temperature protection assembly. The electrical cable electrically connects the electrical power source and the electric motor. The electrical cable extends through at least one thermal zone between the electrical power source and the electric motor. The temperature protection assembly includes a temperature sensor operable to sense a temperature in each thermal zone of the at least one thermal zone. The temperature protection assembly further includes a controller. The controller is configured to determine a zone temperature in the at least one thermal zone.

An airship comprises a plurality of electric power generators; a plurality of electrical buses; and a plurality of propulsion points each equipped with a propellant bundle formed from a plurality of thrusters of the electric-motor-driven propeller type. For each of the propulsion points, a thruster is electrically connected to one of the generators by way of one of the electrical buses, and another thruster of the propulsion point is electrically connected to another of the generators by way of another of the electrical buses.

An airship comprises a plurality of electric power generators; a plurality of electrical buses; and a plurality of propulsion points each equipped with a propellant bundle formed from a plurality of thrusters of the electric-motor-driven propeller type. For each of the propulsion points, a thruster is electrically connected to one of the generators by way of one of the electrical buses, and another thruster of the propulsion point is electrically connected to another of the generators by way of another of the electrical buses.

An aircraft power control device for controlling electric power in an aircraft includes a DC/DC-converter configured for receiving a DC input voltage on a converter input side, converting the received DC input voltage into a DC output voltage and outputting the DC output voltage on a converter output side and an electric power switch is electrically coupled to the converter output side of the DC/DC-converter. The electric power switch is switchable between a switched-on state and a switched-off state. The switch output side is electrically coupled with the switch input side of the electric power switch when in the switched-on state, and wherein the switch output side is electrically isolated from the switch input side of the electric power switch, when in the switched-off state. The system also includes a monitoring device to control the state of the switch.