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 system for emergency shutdown of an electric charger in response to a disconnection is presented. The system includes a computing device, wherein the computing device is configured to receive a sensor datum from a sensor, determine a disruption element between a charging connector and an electric vehicle as a function of the sensor datum, and initiate a disconnection protocol as a function of the disruption element.

A charging connection device for a drone according to an embodiment of the present invention comprises: a core (20) installed on a drone (10); an electrically conductive member (30) positioned on the outer contour of the core (20) and formed o a conductive material; and a tension unit (40) positioned between the core (20) and the electrically conductive member (30) and absorbing shock transmitted from the electrically conductive member (30).

A contactless electrical energy transfer device including a first system which includes at least one first coil including at least one first winding around at least one first zone without wire, a layer of ferromagnetic elements, at least one small column passing through the first coil by passing through a first zone without wire, and a second system which includes at least one second coil including at least one second winding around at least one second zone without wire. The small column or columns make it possible to optimize the magnetic coupling coefficient despite the absence of a layer of ferromagnetic elements in the second system. Also, a flying vehicle fitted with rechargeable batteries and its recharging base, both equipped with the electrical energy transfer device are provided.

A system for establishing a primary function display for an electrical vertical takeoff and landing aircraft. The system further includes a plurality of sensors that detects at least a metric and generates at least a datum based on the at least a metric. Specifically, state of charge is at least generated based on the performance metric of an energy source. The system further includes a display to show the at least a datum. The system further includes a controller that receives the at least a datum and generates a visual to the pilot.

An apparatus 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.

Provided in this disclosure is a high voltage distribution system of an electric aircraft. The system includes a power source mechanically connected to an electric aircraft, where the power source is configured to supply power to the electric aircraft. The system also includes a flight component mechanically connected to the electric aircraft. The system also includes a distribution component configured to control the providing of power to and from the power source and the flight component as needed during recharging and/or operation of the electric aircraft.

A system and method for its use for determining a suitable battery pack combination configured for use in an electric aircraft, the system including at least a processor connected to a sensor and a memory containing instructions configuring the at least a processor to receive battery pack status data for each battery pack of a plurality of battery packs, generate a battery pack diagnostic datum for each battery pack of the plurality of battery packs as a function of the battery pack status data of each battery pack of the plurality of battery packs, and determine a suitability of the plurality of battery packs as a function of each battery pack diagnostic datum for each battery pack of the plurality of battery packs.

A system for monitoring moisture content in a battery pack of an electric aircraft. The system includes a at least an energy storage element, a user interface configured to display moisture content datum to a user, and at least a sensor. At least a sensor is configured detect a moisture content datum of the energy storage element and communicate with the energy storage element. The system also includes a computing device communicatively connected to the at least a sensor. That computing device is configured to generate a notification as a function of the moisture content datum and transmit the notification to a user interface.

A hybrid powertrain system and method includes a prime mover driving a generator/motor to produce an AC power output. The AC power output is applied to a rectifier which is controlled to transform the applied AC power to DC power to supply a DC Power bus at a selected voltage and current. An energy storage device is also connected to the DC power bus and the current flow between the energy storage device and the DC power bus is monitored and compared to preselected values and the results of that comparison are used to alter the operation of the rectifier to increase or decrease, as needed, the current provided to the DC power bus as electrical loads on the DC power bus change.