In accordance with at least one aspect of the present disclosure, there is provided a method for controlling power in an aircraft. The method includes, monitoring an electric energy storage module electrically connected to an electrical bus for an exceedance of a first current limit and monitoring a generator module connected to the electrical bus for an exceedance of a second current limit. If the current limit of either of the electric energy storage module or the generator module is exceeded by a predetermined exceedance amount, the method includes reducing a power consumption for an electric machine by a predetermined bias until the exceedance of the electrical energy storage and the exceedance of the generator module are both less than or equal to zero.

Certain aspects relate to a ground support cart for charging an electric aircraft. An exemplary ground support cart includes a frame, at least a wheel operatively coupled to the frame and configured to facilitate rolling translation of the ground support cart, a cart battery mounted to the frame and configured to provide a first electrical charging current, a conductor in electric communication with the at least a cart battery, a coolant source mounted to the frame and configured to provide a coolant flow, a hose in fluidic communication with the coolant source, and a controller configured to control the first electrical charging current within the conductor and the coolant flow within the hose.

A plurality of energy storage packs (51 to 58) supply a current to a plurality of motor driver (31 to 38) that drive a plurality of motors (21 to 28) mounted on moving object (1), respectively. Sub energy storage pack (59) supplies a current to at least one of a plurality of first current paths connecting the plurality of motor driver (31 to 38) and the plurality of energy storage packs (51 to 58), or pulls a current from at least one of the plurality of first current paths. Controller (70) controls the plurality of first switches (S11 to S18) and the plurality of second switches (S21 to S28) to adjust capacities between the plurality of energy storage packs (51 to 58).

An extravehicular mobility unit (EMU) includes a resonant coil on a surface of the EMU to be coupled to a second resonant coil affixed to a structure via a resonant magnetic field. The EMU also includes a receiver in the EMU coupled to the resonant coil to provide a direct current (DC) voltage based on the resonant magnetic field. A battery in the EMU is charged based on the DC voltage.

Systems and methods associated with electrical systems of aircraft are disclosed. A method disclosed herein comprises generating electricity using an electric generator operatively coupled to an engine of the aircraft, supplying the electricity generated using the electric generator to a baseline power bus; generating electricity using an electric starter generator operatively coupled to the engine; and supplying the electricity generated using the electric starter generator to a supplemental power bus independent from the baseline power bus.

A voltage controlled aircraft electric propulsion system includes an electric propulsion system. The voltage controlled aircraft electric propulsion system may include electric propulsors providing thrust for the aircraft. In hybrid systems, a gas turbine engine may also be included. The electric propulsion system may include at least one electric generator power source, at least one propulsor motor load, and at least one stored energy power source, such as a battery. The propulsor motor load may be supplied power from a power supply bus. The voltage of the power supply bus may be adjusted according to an altitude of the aircraft while maintaining a substantially constant current flow to the propulsor motor load. Due to the adjustment to lower voltages at increased altitude, insulations levels may be lower.

A wireless power delivery system for aircraft seats includes an NFC power receiving device disposed at a known location proximal to floor rail bracket engaging portion of the seat, and an NFC power delivery device engages a corresponding bracket disposed underneath the aircraft floor. The brackets are aligned to each other to ensure the disposition of the NFC power delivery device is sufficiently close to the NFC power receiving device to effectively transfer power. The NFC power delivery device is disposed in a cargo container. Bracket engaging elements in the seat rows include features that indicate a location on a lower bracket to align the NFC power receiving device to the NFC power delivery device.

Aspects relate to a charging station configured to transfer power between an electric aircraft and a power grid via a charging connection. In one or more embodiments, charging station may communicate with the power grid and/or electric aircraft via a communication network. For example, the charging station may be configured to receive a supply request from a power grid or a demand request from an electric aircraft and subsequently generate a control signal that transfers electrical power between the power grid and the electric aircraft via the charging connection.

Flying machines may be docked during charging or other processes. A tray having multiple docking areas is configured to accommodate flying machines for transport and docking. The docking areas may, but need not, include passageways which may accommodate charging stations. For example, a storage enclosure may be configured to house one or more trays, configured to interface to corresponding charging surfaces. Protective layers and vibration dampening features may be used to soften impacts during storage and transport. A charging station may include electrical terminals, recesses, and locating features for docking a flying machine.

A method of generating a customized secondary power distribution assembly (SPDA) includes generating one or more customizable SPDAs. Each of the one or more customizable SPDAs is a construct corresponding with a microprocessor configured to control a set of customizable channels in each of a set of virtual line replaceable modules (vLRMs). The method also includes creating a mapping between one of the one or more customizable SPDAs and the customized SPDA, the mapping indicating line replaceable modules (LRMs) of the customized SPDA and defining each channel of each LRM, and deploying the customized SPDA in an application. The microprocessor is initiated to control the customized SPDA according to the mapping at startup.