A system includes a first power stage circuit having a first PWM input, a first voltage input and a first power output. The first power stage circuit is configured to provide a first current at the first power output responsive to a PWM signal at the first PWM input, and configured to receive a voltage at the first voltage input. The system includes a second power stage circuit having a second PWM input, a second voltage input and a second power output. The second voltage input is coupled to the first voltage input, and the second power stage circuit is configured to provide a second current at the second power output responsive to the PWM signal at the second PWM input. The second power stage circuit is configured to receive the voltage at the second voltage input, the voltage representing an average of the first current and the second current.

A first direct-current to direct-current (DC-to-DC) converter is configured to convert an input direct-current voltage to an output direct-current voltage with a regulated charging current consistent with a target charging current limit or range established by the current estimator for the charging mode and respective cell identifier(s) determined by a cell balancing module for the charging mode for the time interval. A first controller is capable of controlling the charging, individually or collectively, of each of the battery cells by adjusting/controlling the regulated charging current outputted by the first DC-DC converter and/or the duty cycle of switches of the first DC-to-DC converter based on the target charging current limit or range for the time interval.

An electrical power distribution network (306) of an electric power system (300) of an aircraft is operated in at least one normal operation mode such that it provides for load sharing across electrical power sources (A, B, C, D) with respect to electrical loads (AA, BB, CC, DD), wherein the electrical power distribution network (306), in case of an electrical fault, is operated in at least one electrical failure mitigating operation mode, which provides for electric fault isolation, such that a network portion of the electrical power distribution network (306) including the electrical fault is isolated from at least one other network portion of the of the electrical power distribution network.

An electrical power distribution network (306) of an electric power system (300) of an aircraft is operated such that it sequentially adopts a plurality of different partial load sharing modes in a time variable manner, which provide for partial load sharing across electrical power sources (A, B, C, D) with respect to associated electrical loads (AA, BB, CC, DD), by sequentially switching between a plurality of different partial load sharing configurations of the electrical power distribution network, each partial load sharing configuration being associated to a particular one of the partial load sharing modes.

A photovoltaic power generation system and a method for controlling power balance are provided. The system includes at least two photovoltaic arrays, at least one power balance circuit and a power converter. Each of input ports of the power balance circuit is connected with at least one photovoltaic array, and an output port of the power balance circuit is connected with the power converter. The power balance circuit performs power transfer based on a difference between output powers of the two photovoltaic arrays to control a difference between powers of two output terminals of the power balance circuit to be within a preset range.

A method for controlling a vehicle active chassis power system includes determining, via a processor, a minimum output voltage/current threshold for an aggregated power supply associated with an active chassis operation, and generating an aggregate State of Function (SoF) indicative of a maximum voltage/current budget for an output of the vehicle active chassis power system. The aggregate SoF is based on a primary power source voltage/current output and a power storage voltage/current output. The method further includes causing to control an active chassis power system actuator based on a minimum voltage/current value associated with the aggregate SoF. Causing to control the active chassis power system actuator can include publishing the aggregate SoF to a braking actuator, a steering actuator, or to a domain controller that actively distributes an aggregated power supply capability SoF to a braking actuator and a steering actuator based on one or more present vehicle states.

A power management module and method for controlling power consumption of consumers in a wind turbine system. Each power management module in the wind turbine system is configured to determine a voltage level of a power supply bus of the wind turbine system and then control a level of power consumption of one or more consumers coupled to the power supply bus based at least in part on the determined voltage level of the power supply bus. Power consumption may thereby be managed throughout the wind turbine system, without requiring a dedicated centralised controller and communications infrastructure.

Some embodiments provide a DC power distribution system that includes a plurality of DC sources coupled to a plurality of DC buses via respective protection devices that are configured to selectively cause an open-circuit between the DC source and the respective DC bus in the event of a fault or overload condition on the respective DC bus. The plurality of DC buses are coupled to a load combiner, and the system is configured to supply power in parallel from the DC sources via the plurality of DC buses to at least one DC/DC step-down converter via the load combiner, which combines the power supplied via the plurality of DC buses. The DC buses, load combiner, and the DC power sources are configured such that the total maximum load current is capable of being supplied via less than all of the plurality of DC buses in the event that any one of the DC buses is non-operational.

The invention relates to a hybrid propulsion architecture (100) for an aircraft, comprising: —a first source (102) of a first energy type, —second sources (104) of a second energy type different from the first energy type, —electrical propulsion systems (106), —an electric power supply network (118) connecting the first and second sources (102, 104) to the electrical propulsion systems, such that each electrical propulsion system is powered by the first source and by one of the second sources, the architecture being characterised in that it further comprises: —means for segregating (120) the electrical propulsion systems, which means are arranged in the electric power supply network and configured to impose a direction of flow of the electric power from the first source to the electrical propulsion systems.

A power filtration system filters out a common mode signal from a DC conductor of a power system. The power filtration system comprises a first filter and at least one of a load or a power circuit. The first filter is connected to the DC conductor and configured to pass the common mode signal. The load is configured to dissipate the energy of the common mode signal. The power circuit is configured to conduct the common mode signal to an energy storage device.