A power electronics converter includes a multi-layer planar carrier substrate having a plurality of electrically conductive layers, at least one electrical connection, and a converter commutation cell comprising a power circuit and a gate driver circuit. The power circuit includes at least one power semiconductor switching element and at least one capacitor. Each power semiconductor switching element is included in a power semiconductor prepackage having one or more power semiconductor switching elements embedded in a solid insulating material. The power electronics converter includes a heat sink configured to remove heat from the power semiconductor prepackage. A converter parameter η is greater than or 20 equal to 100 kW/m3K, η being defined as a heat transfer coefficient between the heat removal side of the power semiconductor prepackage and a cooling medium of the heat sink divided by the size of a gap between the power semiconductor prepackage and the heat sink.

In an aspect the current disclosure may describe a electric charging station for an electric vehicle. The electric charging station may include a charging cable, wherein the charging cable is configured to carry electricity and an energy source, wherein the energy source is electrically connected to the charging cable. The charging station may further include a temperature sensor, wherein the temperature sensor is configured to generate temperature datum and a computing device. A computing device may be communicatively connected to the plurality of temperature regulating elements and the temperature sensor. The computing device may further be configured to receive the battery datum and regulate battery temperature and cabin temperature using the plurality of temperature regulating elements as a function of the temperature datum.

An apparatus and method for a recharging station including a landing pad, a rechargeable component coupled to the landing pad, and a power delivery unit configured to deliver power from a power supply unit or power storage unit to the recharging component. Rechargeable component includes a plurality of charging units placed at predetermined spacings from one another. The plurality of charging units allows for the electric aircraft to land in any orientation.

An aerial vehicle pertinent to the present application has a rotor system that operates in both a vertical-take-off-landing (VTOL) and a cruise mode. There are boom structures which support rotors and the tail. Tiltable rotors are located at the front ends of the booms. The rear rotors are placed under an upward rise in the booms, which allows for reduced in-flight drag and eliminates the need for collapsible rotors when said rotors are not actively operational.

A system for producing a control signal of an electric vertical take-off and landing (eVTOL) aircraft includes a flight controller configured to obtain a requested aircraft force, generate an optimal command mix, wherein the optimal command mix includes a plurality of commands to a plurality of actuators as a function of the requested aircraft force, wherein generating further comprises receiving an ideal actuator model includes at least a performance parameter, producing a model datum as a function of the ideal actuator model, and generating the optimal command mix as a function of the request aircraft force and the model datum, and produce a control signal as a function of the optimal command mix.

A system for restricting power to a load to prevent engaging a circuit protection device for an electric aircraft includes an energy source. The energy source is communicatively coupled to a load, wherein the load includes a portion of a propulsion system. The system includes sensors configured to sense an electrical parameter. The system includes an aircraft controller communicatively connected to the energy source, wherein the aircraft controller is configured to receive an electrical parameter, compare the electrical parameter to a current allocation threshold, detect that the electrical parameter has reached a current allocation threshold, calculate a power reduction to the load, generate a current allocation threshold notification as a function of the detection, wherein the current allocation threshold notification indicates that the electrical parameter has reached the current allocation threshold. The system includes an electrical circuit including a circuit protection device communicatively connected to the aircraft controller.

An autonomous cargo container retrieval and delivery system locates a select cargo container and maneuvers an unmanned aerial vehicle proximate to the container for retrieval. The vehicle positions itself to engage the cargo container using a grasping mechanism, and, responsive to engaging the cargo container, retracts the cargo container toward the vehicle. As the cargo container is retracted toward the vehicle, weight sensors within the retrieval mechanism sense the weight and the weight distribution of the cargo container, and, can modify the cargo container's location on the vehicle to optimize vehicle flight operations or replace the container on the ground and alert the operator that the cargo container is too heavy or has an improper weight distribution. Upon mating the cargo container with the vehicle, a coupling mechanism latches or secures the cargo container to the vehicle for further flight and/or ground operations.

An autonomous cargo container retrieval and delivery system locates a select cargo container and maneuvers an unmanned aerial vehicle proximate to the container for retrieval. The vehicle positions itself to engage the cargo container using a grasping mechanism, and, responsive to engaging the cargo container, retracts the cargo container toward the vehicle. As the cargo container is retracted toward the vehicle, weight sensors within the retrieval mechanism sense the weight and the weight distribution of the cargo container, and, can modify the cargo container's location on the vehicle to optimize vehicle flight operations or replace the container on the ground and alert the operator that the cargo container is too heavy or has an improper weight distribution. Upon mating the cargo container with the vehicle, a coupling mechanism latches or secures the cargo container to the vehicle for further flight and/or ground operations.

An integrated electric propulsion assembly includes a stator including at least a first magnetic element generating first magnetic field. The assembly includes a propulsor with an integrated rotor, the propulsor further including a hub rotatably mounted to the stator and at least a second magnetic element affixed to the hub, the at least a second magnetic element generating a second magnetic field. At least one of the first magnetic field and the second magnetic field varies with respect to time, wherein the varied magnetic field includes generating a magnetic force between the at least a first magnetic element and the at least a second magnetic element, and the magnetic force causes the hub to rotate with respect to the stator.

A system for producing a control signal of an electric vertical take-off and landing (eVTOL) aircraft includes a flight controller configured to obtain a requested aircraft force, generate an optimal command mix, wherein the optimal command mix includes a plurality of commands to a plurality of actuators as a function of the requested aircraft force, wherein generating further comprises receiving an ideal actuator model includes at least a performance parameter, producing a model datum as a function of the ideal actuator model, and generating the optimal command mix as a function of the request aircraft force and the model datum, and produce a control signal as a function of the optimal command mix.