Aspects relate to a charger for an electric aircraft with failure monitoring and method for its use. An exemplary charger for an electric aircraft with failure monitoring includes a charging circuit. Included within the charging circuit is a connector configured to mate with an electric aircraft port of an electric aircraft and at least a current conductor configured to conduct a current. At least a conductor comprises a direct current conductor configured to conduct a direct current. A charger may include a control circuit configured to command the charging circuit of an electric aircraft as a function of charging datum. A charger may also include a failure monitor circuit, the failure monitor circuit configured to initiate a failure mitigation procedure as a function of a failure of the charging circuit.

A power distribution system includes a bidirectional power converter, a battery, and a controller. The bidirectional power converter is operable to (i) convert AC power received at AC terminals to DC power at DC terminals and (ii) convert DC power received at the DC terminals to AC power at the AC terminals. The bidirectional power converter is disposed within a converter stack formed by a plurality of power converters having DC terminals that are coupled to each other in series. The battery is arranged to be selectively couplable to the DC terminals of the bidirectional power converter. The controller is configured to (i) determine that the DC voltage across the DC terminals of the bidirectional power converter is below a threshold voltage and (ii) couple the battery to the DC terminals of the bidirectional power converter based on the determination that the DC voltage is below the threshold voltage.

A system for regulating charging of an electric aircraft includes a charging connector and a controller communicatively connected to the charging connector. The charging connector includes a housing, at least a conductor, and at least a control signal conductor. The housing is configured to mate with an electric aircraft port of an electric aircraft. The at least a conductor is configured to conduct a current. The at least a control signal conductor is configured to conduct a control signal. The controller is configured to receive a voltage datum from the electric aircraft, and regulate a charging voltage, as a function of the voltage datum, to the electric aircraft. Regulation of the charging voltage includes charging at least a battery of the electric aircraft in a plurality of phases including a first charging phase at a constant current and a second charging phase at a constant voltage.

A monitoring system and method for charging multiple battery packs in an electric aircraft is illustrated. The system includes a plurality of submodules, a power bus element, and a computing device. The plurality of battery submodules is coupled to the electric aircraft and each battery submodules comprises a battery management component which comprises a sensor to detect a health metric. The power bus element is electrically connected to each battery submodule of the plurality of battery submodules. A computing device is connected at each battery submodule and is configured to receive the health metric form the sensor, determine a charging status of the battery submodule as a function of the health metric, and charge the battery submodules using the power bus element as a function of the charging status.

A system and method for a recharging station including a landing pad, a rechargeable component coupled to the landing pad, a power delivery unit configured to deliver powerfrom a power supply unit or power storage unit to the recharging component, and a support component coupled to the bottom of the landing pad.

An electric brake power conversion and distribution system for use in aircraft is provided. An array of DC-DC converters is interposed between a DC power source and a plurality of aircraft electric brake actuators. Each of the DC-DC converters has a characteristic output voltage. The DC-DC converters are interconnected in an additive series of connections to provide an output voltage to the plurality of aircraft electric brake actuators that comprises the sum of the characteristic voltages of the DC-DC converters that are enabled at a particular point in time. A controller manipulates an array of switches interconnected with the array of DC-DC converts, such that the controller can selectively enable or inhibit selected ones of the DC-DC converters, as desired. Accordingly different voltages can be made available for the electric brake actuators depending upon aircraft activity, such as landing, taxiing, parking, or in flight. The invention reduces the size, weight, cost, and associated heat buildup of prior power conversion and distribution systems.

An energy supply system for an electrical seat device in an aircraft or spacecraft comprises a control unit connected to the seat device, an energy supply which is configured to supply the control unit with electrical energy and an energy storage device which is configured to store electrical energy in a rechargeable manner and which is coupled to the control unit such that said energy storage device can be charged by the energy supply and such that the charging and discharging of said energy storage device can be controlled by the control unit, wherein the control unit is configured to use, as required, the electrical energy stored by the energy storage device to operate the seat device.

An electrical system for connecting a rotary electric machine to dc networks operating at different voltages, the electric machine having polyphase winding sets each having a respective index. The electrical system has a first set of ac-dc converter circuits connected in a modular multilevel configuration, each ac-dc converter circuit having a respective index and an ac interface for connection with a corresponding winding set, and in which the modular multilevel configuration has dc outputs each having a respective index. The electrical system also has a set of dc-dc converter circuits each having a respective index and being configured to convert dc power between a voltage at a first dc interface and a voltage at a second dc interface, where a first dc interface of the nth dc-dc converter circuit is connected with the dc outputs of the modular multilevel configuration.

An electric safety circuit for an aircraft DC power supply circuit includes a first electric line connecting a first electric pole of a main DC power supply with a first electric connector of an electric load; a second electric line connecting a second electric pole of the main DC power supply with a second electric connector of the electric load; at least one electric safety switch arranged in at least one of the first and second electric lines and configured for selectively interrupting any electric current flowing through said at least one electric line; a first electric coil arranged in the first electric line.

A connector with overvoltage protection, and methods of use, for charging an electric aircraft. The connector includes a housing, at least a current conductor, a protection circuit, at least a sensor and a controller. The housing is configured to mate with an electric aircraft port of the electric aircraft. The at least a current conductor is configured to conduct a current. The protection circuit is configured to control transmission of electrical power through the connector. The at least a sensor is configured to detect an output voltage of the connector. The controller is communicatively connected to the at least a sensor. The controller is configured to determine an overvoltage output as a function of the output voltage, and activate the protection circuit based on detection of the overvoltage output.