An electrically powered unmanned aircraft system (UAS or drone) including a propeller including a core formed by battery material layers as a power source and integrated as a structural component of the drone. The battery material layers can be a graphene super capacitor or a nanopore battery structure. Power available from the integrated battery material layers can be used to power an electric motor included with the drone and operating to rotate the propeller.

A power system is provided. The power system includes: an electric machine comprising a first multiphase winding and a second multiphase winding, the first multiphase winding and the second multiphase winding being electrically opposite in phase with respect to one another; and a power converter system having: first switching elements in electric connection with the first multiphase winding and having a DC side and an AC side; second switching elements in electric connection with the second multiphase winding and having a DC side and an AC side; a plurality of capacitors coupled to the first switching elements on the DC side of the first switching elements and to the second switching elements on the DC side of the second switching elements; and a means for reducing common mode currents on the AC side of the first switching elements and on the AC side of the second switching elements.

A power system is provided. The power system includes: an electric machine comprising a first multiphase winding and a second multiphase winding, the first multiphase winding and the second multiphase winding being electrically opposite in phase with respect to one another; and a power converter system having: first switching elements in electric connection with the first multiphase winding and having a DC side and an AC side; second switching elements in electric connection with the second multiphase winding and having a DC side and an AC side; a plurality of capacitors coupled to the first switching elements on the DC side of the first switching elements and to the second switching elements on the DC side of the second switching elements; and a means for reducing common mode currents on the AC side of the first switching elements and on the AC side of the second switching elements.

A hybrid propulsion unit for an aircraft with multi-rotor rotary wings includes an electrical generator driven by an internal combustion engine, a rectifier configured to convert an AC current sent by the electrical generator into DC current, a DC-AC converter, an electrical network connecting the rectifier to the converter and including a high-voltage DC current bus, electric motors powered by propeller converters coupled to the electric motors, electrical energy storage connected to the electrical network, the electrical storage including at least one primary storage element and at least one secondary storage element.

An electric power system for a vehicle includes at least one electric machine, one or more power rectifiers, and a plurality of DC channels. The at least one electric machine includes a plurality of tooth-wound multi-phase windings that are substantially magnetically decoupled, and the at least one electric machine is mechanically balanced even if one of the plurality of windings is de-energized. The one or more power rectifiers are configured to produce rectified power from the power generated by the at least one electric machine. The plurality of DC channels are formed after the at least one power rectifier and are configured to provide DC power to one or more loads within a vehicle.

A power and energy management (PEM) method for managing power consumed by a plurality of power devices on a network. The method includes: a monitoring step (S1) to determine whether PEM is required based on the power available on the network and the power consumption of the power devices on the network; a monitor step (S2) to determine the operating status of each of the power devices on the network; a step (S4) of determining a strategy for operating the power devices in response to a determination in the monitoring step that PEM is required; a step (S5) of determining a coordination strategy for recharging of any storage devices on the network in response to a determination in the first network monitoring step that PEM is not required; and controlling (S6) devices on the network to operate at a power consumption level and/or to recharge based on the above steps.

A power and energy management (PEM) method for managing power consumed by a plurality of power devices on a network. The method includes: a monitoring step (S1) to determine whether PEM is required based on the power available on the network and the power consumption of the power devices on the network; a monitor step (S2) to determine the operating status of each of the power devices on the network; a step (S4) of determining a strategy for operating the power devices in response to a determination in the monitoring step that PEM is required; a step (S5) of determining a coordination strategy for recharging of any storage devices on the network in response to a determination in the first network monitoring step that PEM is not required; and controlling (S6) devices on the network to operate at a power consumption level and/or to recharge based on the above steps.

An electrical propulsion system comprises an inverter, an electrical motor assembly, an assembly, and a rotor position sensor. The inverter comprises a printed circuit board assembly (PCBA). The electrical motor assembly comprises a stator and a rotor. The assembly is configured to rotate a propeller and comprises a moving component and a stationary component. The rotor position sensor comprises at least one sensor coupled to the PCBA, and a magnet located on the moving component. The at least one sensor is configured to detect a magnetic field of the magnet through the stationary component.

A joint assembly for an aircraft comprising: a joint comprising a first portion rotatably coupled to a second portion so that the first portion can rotate relative to the second portion; an actuator for rotating the first portion of the joint and comprising a connecting portion that connects to the first portion of the joint; and a latch moveable to a latched arrangement in which the latch prevents rotation of the first portion of the joint in at least one rotational direction, the latch being biased toward the latched arrangement and operatively connected to the connecting portion such that if the connecting portion becomes separated from the rest of the actuator, the latch moves to the latched arrangement, thereby preventing rotation of the first portion of the joint in the at least one rotational direction.

A joint assembly for an aircraft comprising: a joint comprising a first portion rotatably coupled to a second portion so that the first portion can rotate relative to the second portion; an actuator for rotating the first portion of the joint and comprising a connecting portion that connects to the first portion of the joint; and a latch moveable to a latched arrangement in which the latch prevents rotation of the first portion of the joint in at least one rotational direction, the latch being biased toward the latched arrangement and operatively connected to the connecting portion such that if the connecting portion becomes separated from the rest of the actuator, the latch moves to the latched arrangement, thereby preventing rotation of the first portion of the joint in the at least one rotational direction.