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 vertical takeoff and landing (VTOL) aircraft, including: a vehicle controller circuit programmed to operate the VTOL aircraft without an onboard human operator; a rotor system; an airframe; and an external cargo coupling to receive an external payload of at least approximately 300 pounds beneath the airframe.

In an aspect of the present disclosure is a computing device for predicting battery temperature in an electric aircraft, the computing device including a controller communicatively connected to the electric aircraft, the controller comprising: a battery model, the battery model configured to: receive a flight plan; instantiate a machine-learning model, wherein the machine-learning model is trained as a function of a training set correlating flight plan data to battery temperature labels.

A locking system for an electric propulsion system is disclosed. The system includes a propulsor configured to propel an electric vehicle and a motor operatively connected to the propulsor configured to power the propulsor. The motor includes a rotor connected to the propulsor and a stator configured to rotate the rotor. A propulsor sensor is configured to determine a motion parameter of the propulsor. A lock is configured to prevent a movement of the propulsor. A controller is configured to receive a signal from the propulsor sensor and control the motor as a function of the signal from the propulsor sensor, wherein controlling the motor includes allowing the propulsor to slow at a desired rate for parking.

Systems and methods relate to electric propulsor fault detection. An exemplary system includes at least a first inverter configured to accept a direct current and produce an alternating current, a first propulsor, a first motor operatively connected with the first propulsor and powered by the alternating current, and at least a noise monitoring circuit electrically connected with the direct current and configured to detect electromagnetic noise and disengage the at least an inverter as a function of the electromagnetic noise.

Aircraft with battery thermal regulation systems, including: an aircraft air inlet and an aircraft air outlet; a battery pack including battery cells; and a battery thermal regulation system including a first air channel, a surface of which is in thermal communication with the battery cells so that air flowing through the first air channel exchanges heat with the cells through the surface; and an airflow device for driving an airflow. The battery thermal regulation system has a first and a second mode operation. In the first mode, the first air channel is fluidly connected with the aircraft air inlet and the aircraft air outlet whereby, during flight of the aircraft, air can enter the aircraft through the air inlet, flow through the first air channel and exit the aircraft through the air outlet. In the second mode, the airflow device drives an airflow through the first air channel.

This method is for manufacturing a fan blade rotor which includes an annular rotation support ring around a rotary shaft, a permanent magnet provided alongside the rotation support ring in the radial direction, and a composite material for integrally binding the rotation support ring and the permanent magnet, the method including: a step S1 for arranging the rotation support ring and the permanent magnet side by side in the radial direction; steps S2-S4 for spirally winding, on the rotation support ring and the permanent magnet arranged side by side being as a core, the composite material being an uncured composite material including a reinforcement fiber impregnated with an uncured resin with the fiber direction of the reinforcement fiber set as a longitudinal direction; and a step for curing the resin included in the composite material.

An abnormality diagnosis system performs an abnormality diagnosis of a plurality of motor systems that include a motor for moving a moving body. The abnormality diagnosis system identifies a comparison target system that is the motor system, among the motor systems, that is a comparison target in relation to a diagnosis target system that is the motor system to be a target of the abnormality diagnosis. The abnormality diagnosis system acquires a state-related value that is a value related to an operation state of the motor from each of the diagnosis target system and the comparison target system. The abnormality diagnosis system performs a comparison of the state-related value that is acquired from the diagnosis target system and the state-related value that is acquired from the comparison target system, and diagnoses a presence or absence of an abnormality in the diagnosis target system using a result of the comparison.

Method and system to ascertain location of drone box for landing and charging drones comprising at least a drone box having a drone platform with a plurality of limiting boundaries, divided into number of sensor zones that are mechanically contiguous and electrically separated by an insulated separator of insulation width, each sensor zone having an identification coordinates, each drone having a plurality of ground interfaces, each having a unique address code, each ground interface has a charging terminal at a far end, each charging terminal having an interlocked switchable electricity polarity. The identification coordinates of the activated sensor zones are communicable to a second drone so that the second drone knows where NOT to land on the drone box, Such communication enables a third and subsequent drone to ascertain whether the identified drone box is suitable and available for landing.