A method for managing power drawn from power units of propulsion units of an aircraft, wherein the method includes a step of increasing the amount of power drawn from a second power unit that is time shifted, with respect to a step of increasing the amount of power drawn from a first power unit, for a duration that at least allows the operational state or the non-operational state of the first power unit to be determined. This solution allows simultaneous switching to the non-operational state of the two power units to be avoided.

The DC electrical network comprises an electrical load supplied with electricity by an electrical power source to which the electrical load is linked by a first electrical line and a second electrical line. An overcurrent protection system comprising an input pole and an output pole is mounted in series on the first electrical line. The overcurrent protection system comprises an electronic switch mounted in series between the input pole and the output pole, an electrical current sensor, and a controller configured to control the electronic switch. It also comprises an electronic device linked to the input pole and to the second electrical line. The controller is configured to command a conducting state of the electronic device when a current measurement from the electrical current sensor is above a predetermined current threshold, then to command an opening of the electronic switch.

An example system includes one or more battery modules, a battery module of the one or more battery modules comprising: a cylindrical pressure vessel; a cooling channel extending axially through the cylindrical pressure vessel; and one or more battery packs within the cylindrical pressure vessel, a battery pack of the one or more battery packs comprising a plurality of battery cells radially distributed about the cooling channel.

An electric propulsion system includes at least one generator. The electric propulsion system also includes at least one drive engine coupled to the at least one generator. The electric propulsion system further includes at least one electrical device. The electric propulsion system also includes at least one battery integrated isolated power converter (BIIC), where the at least one generator and at least one of the at least one BIIC and the at least one electrical device are coupled, and where the at least one BIIC and the at least one electrical device are coupled.

An electric power supply system for an aircraft includes: a first electric source and a second electric source coupled together to supply electric power to a set of electrical loads, and a controller configured to acquire a piece of information on the current electric consumption consumed by the set of electrical loads; acquire a piece of information corresponding to a target ratio of the distribution, between the first and second electric sources, of the current electric consumption consumed by the set of electrical loads; perform frequency filtering of the current electric consumption to determine a transient consumption portion of the current electric consumption; determine control setpoints for the first electric source and for the second electric source in accordance with the target distribution ratio and with the transient consumption portion; and apply the control setpoints to the first and second electric sources.

A temperature monitoring apparatus configured to monitor a temperature of a portion of a vehicle's electrical energy distribution network is disclosed. The apparatus includes a first optical fibre including one or more temperature sensing sections, each temperature sensing section being for thermal contact with a portion of a vehicle's electrical energy distribution network. Each temperature sensing section is arranged to produce, in response to an optical input signal, an optical output signal indicative of the temperature of the temperature sensing section. The apparatus is arranged to determine a temperature of the portion of the vehicle's electrical energy distribution network based on one or more of the output optical signals in use.

On an aircraft, a multi-mode power generator is operated in a variable voltage mode to power an electric Wng Ice Prevention System (eWIPS), and is operated in a fixed voltage mode to provide backup power. When atmospheric conditions are conducive to the formation of ice (and main generators are operative), the multi-mode power generator is operated in variable voltage mode to power the eWIPS with a first or second variable voltage. The first variable voltage, the value of which depends on atmospheric conditions, is for anti-ice operation. The second variable voltage, which can be the maximum output voltage, is for de-ice operation. Transitions between different variable voltage levels are not instantaneous which eliminates fatigue damage due to transients. If a main generator fails (or when atmospheric conditions are not conducive to the formation of ice), the multi-mode power generator is operated in fixed voltage mode to provide backup power.

For aircraft taxiing, an aircraft is equipped with an electric machine installed in a propulsor gearbox (PGB), in parallel to the gas turbine, working in motor mode during taxi, and in generator mode during flight phases (such as take-off, climb, cruise, descent, approach and landing). Typical current systems which use an electric machine in the PGB do not use the electric machine in motor mode for taxi operations (i.e., it is only an additional generator). An optimized power supply providing a combination of a thermal engine such as an Auxiliary Power Unit (APU) and an electric energy storage system such as a battery provides power to the PGB electric machine even when the gas turbine is off.

An unmanned aerial vehicle according to the present invention includes: a main body; an arm that extends from the main body to support a rotor; a first electrical conductor which is supported by the arm and to which a voltage is applied; a second electrical conductor which is supported by the arm and spaced apart from the first electrical conductor and to which a voltage lower than the voltage applied to the first electrical conductor is applied; and a controller configured to control electrical supply to the first and second electrical conductors.

A power supply system includes a set of power supply units, each power supply unit arranged electrically in series and defining a common power supply, each power supply unit having a power module and a selective bypass for selectively bypassing the respective power module. The power supply system can meet a power demand.