A drive system comprises a DC-DC converter that is arranged to receive an input voltage from a battery having a nominal battery voltage. The DC-DC converter has a first mode of operation in which the DC-DC converter generates a regulated output voltage from the input voltage and supplies the regulated output voltage to a load, and a second mode of operation in which the DC-DC converter is by-passed such that the input voltage from the battery is supplied to the load. A controller is arranged to compare the input voltage to a threshold voltage that is less than the nominal battery voltage. The controller operates the DC-DC converter in the first mode when the input voltage is less than the threshold voltage, and operates the DC-DC converter otherwise.

The battery thermal management system includes a battery pack, a circulation subsystem, and a heat exchanger. The system can optionally include a cooling system, a reservoir, a de-ionization filter, a battery charger, and a controller.

A system for preconditioning a power source of an electric aircraft is presented. The apparatus includes a power source of an electric aircraft, a computing device, and a user device. The computing device is configured to receive a flight plan, determine a predicted power usage model as a function of the flight plan, and initiate a power source modification on the electric aircraft as a function of the predicted power usage model. The user device is configured to display a flight performance infographic as a function of the predicted power usage model.

In an aspect, a system for recharging an electric vehicle. A system includes an electric vehicle. An electric vehicle includes at least a propulsor. An electric vehicle includes a recharging connector electrically connected to a power source. An electric vehicle includes a power storage unit. A power storage unit is configured to store power. An electric vehicle includes a power supply circuit. A power supply circuit is in electric communication with a power storage unit and recharging connector. A power supply circuit includes a buck-boost regulator. A buck-boost regulator includes at least an inductor. A buck-boost regulator includes a switching device to supply intermittent current to at least an inductor. At least one of at least an inductor and a switching device is a component of at least a propulsor motor.

Technology for operating an engine smoothly is provided. In an aircraft propulsion system, a controller causes at least a first engine among the plurality of engines to be stopped and causes a second engine, which has not been stopped, to be operated when an aircraft is flying in a prescribed flight mode and causes the first engine to be operated and causes the second engine to be stopped when a detector detects that the temperature related to the first engine is less than or equal to a first prescribed temperature.

Certain aspects relate to a battery pack for electric vertical take-off and landing aircraft. Exemplary battery pack includes a first pouch cell, a second pouch cell, at least a sensor, where the at least a sensor is configured to sense battery pack data and transmit the battery pack data to a data storage system, and a vent configured to vent the ejecta from the first pouch cell. In some embodiments, battery pack may be configured to power at least a propulsor component.

In one embodiment, an apparatus for redundant control of active fuses for battery pack safety is provided, comprising a battery; an electrical load coupled to the battery via a fuse capable of being activated by an electrical signal; a sensor configured to sense a short circuit condition at the electrical load and output an analog sensor signal; an analog-to-digital converter configured to sample the analog sensor signal and output a digital sensor signal; a microcontroller configured to detect the short circuit condition at the electrical load based on the digital sensor signal, and, during normal operation, to output a first electrical signal to activate the fuse after detecting the short circuit condition at the electrical load; and an analog circuit configured to operate independently of the microcontroller to receive the analog sensor signal and output a second electrical signal to activate the fuse after receiving the analog sensor signal.

A helicopter may include a hybrid engine system including an internal combustion engine (e.g., a turbine engine) and an electric engine. The internal combustion engine and the electric engine being coupled to the rotor system and configured to separately or collectively operate the rotor system in response to a triggering event. In one aspect, a method for operating a rotor system of a helicopter may include receiving an indicator of a triggering event and actuating a non-active engine, one of the internal combustion engine or the electric engine, in response to receiving the triggering event.

In an aspect, a system for recharging an electric vehicle. A system includes a recharging component. A recharging component includes a ventilation system. A system includes a sensor configured to detect a plurality of data from the recharging component. A sensor is configured to generate an environment datum as a function of the plurality of data. A system includes a control pilot. A control pilot is in electronic communication with a sensor. A control pilots is configured to receive an environment datum from a sensor. A control pilot is configured to generate a ventilation requirement datum from an environment datum. A control pilot is configured to command a recharging component to perform a ventilation process. A system includes a pilot display. A pilot display is coupled to an electric vehicle. A pilot display is configured to display a ventilation requirement datum to a pilot.

According to at least one exemplary embodiment, a method, system and apparatus for an aircraft may be shown and described. An exemplary embodiment may be an autonomous aircraft which can vertically takeoff and land (VTOL). The VTOL aircraft may have a modular pod which carries a removable payload. The entire VTOL aircraft may be portable. An exemplary embodiment may fit into a standard sized freight container. A propulsion system may be based on distributed electric propulsion. An exemplary embodiment may implement variable pitch propellers and collective pitch variation.