An aircraft and method, including a power distribution network and a set of dischargeable power system modules. The dischargeable power system module can include a chassis, a set of replaceable dischargeable energy modules selectively interconnected within the chassis, and an energy management module having a controller module configured to operably control the power distribution from the set of energy modules during aircraft operations, based on the energy demands of the respective subset of the power-consuming subsystems.

An aircraft and method, including a power distribution network and a set of dischargeable power system modules. The dischargeable power system module can include a chassis, a set of replaceable dischargeable energy modules selectively interconnected within the chassis, and an energy management module having a controller module configured to operably control the power distribution from the set of energy modules during aircraft operations, based on the energy demands of the respective subset of the power-consuming subsystems.

An electric power conversion system comprising: an alternating current (AC) source comprising a plurality of AC terminals for conducting AC power; a voltage source electrically coupled to the AC terminals; and a controller operably coupled to the voltage source, the controller being configured to: operate the voltage source to apply a fault reducing voltage at the AC terminals that reduces an AC line-to-line fault current (I.sub.f).

An electric power conversion system comprising: an alternating current (AC) source comprising a plurality of AC terminals for conducting AC power; a voltage source electrically coupled to the AC terminals; and a controller operably coupled to the voltage source, the controller being configured to: operate the voltage source to apply a fault reducing voltage at the AC terminals that reduces an AC line-to-line fault current (I.sub.f).

Unmanned aerial vehicles are provided. In one aspect, the unmanned aerial vehicle includes a four-bar linkage mechanism in mechanical communication with a pair of wings. An electrical subsystem includes an actuator in mechanical communication with the four-bar-linkage mechanism. The actuator is in electrical communication with a capacitor. A plurality of solar panels is in electrical communication with the capacitor, which is configured to harvest non-battery energy from the plurality of solar panels to power the actuator for controlling the four-bar linkage mechanism to operate the pair of wings.

Unmanned aerial vehicles are provided. In one aspect, the unmanned aerial vehicle includes a four-bar linkage mechanism in mechanical communication with a pair of wings. An electrical subsystem includes an actuator in mechanical communication with the four-bar-linkage mechanism. The actuator is in electrical communication with a capacitor. A plurality of solar panels is in electrical communication with the capacitor, which is configured to harvest non-battery energy from the plurality of solar panels to power the actuator for controlling the four-bar linkage mechanism to operate the pair of wings.

A power electronics converter may include: a converter commutation cell having a power circuit and a gate driver circuit, the power circuit including at least one power semiconductor switching element and at least one capacitor, wherein each power semiconductor switching element is embedded in a solid insulating material, wherein each power semiconductor switching element has at least three terminals including a gate terminal, wherein the gate driver circuit is electrically connected to and configured to provide switching signals to the gate terminal of each power semiconductor switching element, wherein a peak rated power output of the power electronics converter is greater than 25 KW, and wherein a total rated capacitance of the power circuit of the converter commutation cell divided by the peak rated power output of the power electronics converter is less than or equal to 5 nF/W.

A power electronics converter may include: a converter commutation cell having a power circuit and a gate driver circuit, the power circuit including at least one power semiconductor switching element and at least one capacitor, wherein each power semiconductor switching element is embedded in a solid insulating material, wherein each power semiconductor switching element has at least three terminals including a gate terminal, wherein the gate driver circuit is electrically connected to and configured to provide switching signals to the gate terminal of each power semiconductor switching element, wherein a peak rated power output of the power electronics converter is greater than 25 KW, and wherein a total rated capacitance of the power circuit of the converter commutation cell divided by the peak rated power output of the power electronics converter is less than or equal to 5 nF/W.

An energy management system and method of operating the energy management, which include estimating an energy demand for flight plans for a fleet of aircraft. The flight plans are received from a flight plan database. The system is configured to determine whether a set of dischargeable energy modules are locatable at a respective location of a subset of the fleet of aircraft based at least in part on a replaceable power source inventory database or the subset of the plurality of flight plans. The system is configured to generate a power source inventory distribution plan allocating a subset of dischargeable energy modules for the subset of the plurality of flight plans for the fleet of aircraft based at least in part on the determination that the set of dischargeable energy modules are locatable at the respective location of the subset of the fleet of aircraft.

A method for manufacturing a rotor assembly of an electric engine, comprising: loading a first and second plurality of magnets in a magnet insertion tool, loading a sleeve in the magnet insertion tool: performing an insertion movement of the first plurality of magnets with respect to the second plurality of magnets using the magnet insertion tool, wherein the insertion movement comprises: moving the first plurality of magnets in a radial direction of the sleeve; moving the second plurality of magnets in an axial direction of the sleeve; and expanding a radius of the sleeve in the radial direction using the magnet insertion tool during the insertion movement.