Aircraft electric power distribution systems and methods of operating aircraft electrical power distribution systems are provided. One such method comprises determining a measure of an electrical power demand of a power and propulsion system of the aircraft; setting a target operating voltage of the aircraft electrical power distribution system based at least in part on the measure of the electrical power demand; and controlling the operating voltage in accordance with the set target operating voltage. In some embodiments the measure of the electrical power is a measure of an operating parameter of a gas turbine engine or propulsor of the aircraft.

A structure and equipment system installed in an aircraft includes vertical supports, a rail device, a connector, guiding elements, pivot joints, and locking devices. The rail device is arranged on the aircraft to guide the guiding elements along a rail device extension axis. Via the connector, the vertical supports are arranged in parallel and connect to form a grid arrangement with the guiding elements arranged thereon. The pivot joints are attached to upper ends of the vertical supports to pivot them. The locking devices each have a first and a second locking element. The grid arrangement is inserted into the aircraft as far as an installation position via the guiding elements on the rail device with vertical supports pivoted upwards from the vertical, by pivoting down into a vertical orientation, the first locking elements can interlock with correspondingly arranged second locking elements to form a load-bearing support structure.

A vehicle, including a high voltage energy consumer; an electrical energy source; an electrical energy distribution network having an electrical energy distribution element configured to carry electrical power from the electrical energy source to the high voltage energy consumer; and a cooling system for cooling the high voltage energy consumer, the cooling system having: coolant, and a coolant distribution network having a coolant distribution element for delivering the coolant to the high voltage energy consumer to remove heat generated by the high voltage energy consumer; wherein the coolant distribution element provides mechanical support to the electrical energy distribution element, and the coolant within in the coolant distribution element removes heat generated in the electrical energy distribution element as it carries electrical power from the electrical energy source to the high voltage energy consumer

A first portion of a series battery is arranged where the first portion of the series battery produces a first magnetic field and the series battery includes a plurality of charge storage devices, a negative output terminal, a positive output terminal, and a plurality of intradevice connections connecting the plurality of charge storage devices in series. A second portion of the series battery is arranged such that a second magnetic field produced by the second portion of the series battery at least partially cancels out the first magnetic field.

A condition of an unmanned aerial vehicle (UAV) is detected using one or more sensors of the UAV and signaled according to an alert definition associated with the condition. For example, an alert definition can indicate to signal the condition by using a motor of the UAV to produce an audible tone. A tonal signal having a frequency within an audible spectrum can be generated according to the alert definition. The tonal signal and a drive signal used for supplying current to the motor can be combined to produce a combined signal. The combined signal can then be transmitted to the motor to cause the motor to produce the audible tone. In some cases, an amplitude of the tonal signal can be modulated, such as where the amplitude of the combined signal exceeds a threshold associated with an operating margin of the UAV.

A power supply system includes a rotor for generating at least one of lift or thrust of an aircraft, a component group formed of a plurality of electrical components for rotating the rotor, and a battery for supplying power to the component group. The rotor includes a VTOL rotor and a cruise rotor, and the component group includes a VTOL component group and a cruise component group. The VTOL component group and the cruise component group are supplied with power from the same battery.

An energy storage system used in a flight vehicle includes: a plurality of energy storage apparatuses; and a power transfer circuit that is connected to the plurality of energy storage apparatuses and transfer electric power between the plurality of energy storage apparatuses.

A system for battery management for electric aircraft batteries includes an energy storage system configured to provide energy to the electric aircraft via a power supply connection, the energy storage system including: a battery pack, a sensor configured to detect a condition parameter of the battery pack and generate a battery datum based on the condition parameter, a pack monitoring unit (PMU) configured to receive the battery datum, and a high voltage disconnect configured to terminate the power supply connection between the battery pack and the electric aircraft; a high voltage bus electrically connected to the high voltage disconnect; a primary functional display configured to display information based on battery datum; and a first controller area network (CAN) bus and a second CAN bus communicatively connected to the PMU, the high voltage bus, and the primary functional display.

A connector with ambience monitoring capability for charging an electric aircraft. The connector includes a housing, at least a current conductor, at least a ground conductor and at least a control pilot. 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 at least a ground conductor is configured to conduct to ground. The at least a control pilot is configured to conduct a control signal. The at least a control pilot is further configured to receive a voltage datum of a battery of the electric aircraft, determine, as a function of the voltage datum, an ambient requirement for the battery, and transmit the ambient requirement for implementation. A method, of using a connector with ambience monitoring capability, for charging an electric aircraft is also provided.

A main electrical cabling is subject to variations in ambient temperature over its length. A detection system for detecting fault in the main electrical cabling able to cause a serial arc, or heating within a connection, includes a monitor electrical cabling placed as a return loop alongside the main electrical cabling, a monitoring device, and a return cable bringing back electrical potential at the output of the main electrical cabling to the monitoring device. The monitoring device includes a controllable current generator injecting, into the monitor electrical cable, a current dependent on current flowing through the main electrical cabling. Electronic circuitry determines a difference in voltages at inputs and outputs of the main electrical cabling and of the monitor electrical cabling, to detect a potential fault in the main electrical cabling leading to a serial arc or increase in temperature. A fault in the main electrical cabling is detected despite variations in temperature.