Abstract: A system and method for speed control as a function of battery capability in an electric aircraft is illustrated. The system comprises a battery pack coupled to the electric aircraft, a sensor coupled to the battery pack and configured to detect a battery pack output, and a computing device coupled to the sensor. The computing device is configured to receive the battery pack output from the sensor and adjust a maximum speed of the electric aircraft as a function of the battery pack output and a battery pack output threshold.

Abstract: In an aspect, a system for battery temperature management in an electric aircraft. In some embodiments, the system includes a plurality of battery cells, comprised of pouch cells. The system includes at least a sensor communicatively connected to a computing device. At least a sensor may be configured to detect temperature. A system also includes a plurality of temperature regulating elements disposed between the plurality of pouch cells. A temperature regulating elements are configured to maintain the temperature of the battery pack. The system also includes a computing device communicatively connected to the plurality of temperature regulating elements. A computing device is configured to determine a target temperature of the plurality of cells and direct the plurality of temperature regulating elements to modify a temperature of the plurality of battery cells as a function of the target temperature.

Abstract: Electric aircraft charging system including charging cable configured to carry electricity and energy source, wherein the energy source is electrically connected to the charging cable. The system also including a cable reel module, the cable reel module including a reel, wherein the reel is rotatably mounted to the cable reel module, wherein the reel is configured to rotate in a forward direction and a reverse direction, and the charging cable, in a stowed configuration, is wound around the reel. The cable reel module further including a rotation mechanism configured to rotate the reel in reverse, and a cable reel module door having a closed position and an open position, wherein the closed position prevents access to the reel and the open position allows access to the reel. The system additionally including a controller communicatively connected to the rotation mechanism and configured to send a retraction signal to the rotation mechanism.

Abstract: In an aspect an apparatus for encrypting external communication for an electric aircraft. The apparatus may comprise a communication component configured to communicate with a network node. The apparatus may also include a battery pack configured to power the electric aircraft and a battery sensor, wherein a battery senor is configured to generate battery datum. A computing device may be included within the apparatus. The computing device may be configured to be receive the battery datum, encrypt the battery datum using an encryption process, identify the network node and transmit the encrypted battery datum to the network node using the communication component.

Abstract: A device for emergency disconnection of a high voltage electrical connection between a power source and a high voltage component of an electric aircraft in response to a crash. The device includes a controller, where the controller is configured to receive a sensor datum from a sensor of device, to determine a crash element between and initiate a disconnection protocol as a function of the crash element.

Abstract: Provided in this disclosure are components and methods for diagnostic and communication for an electric aircraft. Components may include a diagnostic element connected to a flight component which may include a sensor and a diagnostic circuit. Component may detect a module datum, maintenance phenomenon, maintenance datum, and flight status. Flight status may be transmitted to a remote device accessible by a user.

Abstract: In an aspect this disclosure is directed at a propulsor assembly powered by a dual motor system. The aircraft may comprise a propulsors. The electric aircraft may also include a driveshaft that is mechanically coupled to the propulsor, wherein a driveshaft is configured to provide mechanical power to the propulsor. The aircraft includes a plurality of electric motors. The electric motors may be configured to impart rotational energy to the driveshaft. Wherein each electric motor includes a stator and a rotor. Each electric motor is selectively engaged to the driveshaft by a freewheel clutch.

Abstract: 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.

Abstract: In an aspect the present disclosure is directed to an electric aircraft. An electric aircraft may include a plurality of fixed wings, a tail, a first boom, and a second boom and a plurality of lift components. The aircraft also includes a tail affixed to the aft end of the fuselage, a first boom including a first rear end affixed to the tail and a first forward end proximal to the fore end of the fuselage, wherein the first boom is affixed to a first wing, a second boom including a second rear end affixed to the tail and a second forward end proximal to the fore end of the fuselage, wherein the second boom is affixed to the second wing. The aircraft may include a plurality of lift components which may be affixed to the booms.

Abstract: Aspects relate to systems and methods for manufacture of a battery pack including a metal case circumscribing an inner volume circumscribed on all but one open side, where the case additionally includes a sealing rim positioned at least partially about the open side, a first component that includes at least two or more sides of the case, and a second component that includes at least one other side of the case, at least a battery module installed within the inner volume of the case, and an inner panel installed within the inner volume, between the case and the at least a battery module. In some aspects, sealing rim, first component, and second component are all joined together by welding.

Abstract: A fuel-based flight indicator apparatus for an electric aircraft is illustrated. The apparatus comprises a flight indicator and a computing device communicatively connected to the flight indicator, wherein the computing device is configured to receive a battery datum from a battery sensor located in the electric aircraft, receive an environmental datum from an environmental sensor located in the electric aircraft, determine an indicator datum as a function of the battery datum, the environmental datum, and a flight plan, and display the indicator datum on the flight indicator.

Abstract: The present invention is directed to an apparatus for managing thermal energy of an electric aircraft energy source. Apparatus may include fins, which extend from a skin of electric aircraft. The energy source may bias or be adjacent to the fins so that heat energy may dissipate from the energy source and through the fins and, thus, the skin. A coolant may also be run through the apparatus, where the coolant may flow through channels that are disposed between the fins.

Abstract: A system and method for an electric aircraft coaching simulator is illustrated. The simulator includes a pilot control that is configured to generate a pilot command. The simulator includes a processor that is configured to receive optimized flight data, simulate a battery performance of an electric aircraft as a function of the received pilot command and generate an optimal flight recommendation based off the optimized flight data. The simulation model is configured to communicatively connect with the flight simulator to mimic a real flight situation. Optimized flight data from other pilots can be used to coach pilots how to fly with more energy efficiency.

Abstract: A apparatus for fault detection for use in an electric aircraft is disclosed herein. The apparatus includes a battery module with a plurality of battery cells, a plate extending along the row of cells, insulation between the plate and the plurality of cells, a sensor configured to detect a potential signal, and a controller communicatively connected to the sensor. The controller is configured to receive the potential signal and determine a fault.

Abstract: A system and method for the remote piloting of an electric aircraft is illustrated. The system comprises a remote device located outside an electric aircraft, wherein the remote device is configured to receive a flight command input from a user and transmit the flight command input to a flight controller located on the aircraft. The flight controller is located inside the aircraft and configured to receive the flight command input from the remote device and enact the flight command autonomously as a function of the flight command input.

Abstract: A system for determining areas of discrepancy in flight for an electric aircraft is presented. The system includes a plurality of sensors, wherein each sensor is communicatively connected to a flight component and configured to detect a measured flight and generate a flight phase datum. The system further includes a computing device communicatively connected to the plurality of sensors, wherein the computing device is configured to determine, by a flight phase machine-learning model, a flight phase discrepancy datum. The computing device is configured to train the flight phase machine-learning using a flight phase training set, wherein the flight phase training set correlates a flight phase to a flight standard and output the flight phase discrepancy datum. The computing device is further configured to identify an anomalous performance phase as a function of the flight phase discrepancy datum and generate a discrepancy response.

Abstract: A system and method for speed control as a function of battery capability in an electric aircraft is illustrated. The system comprises a battery pack coupled to the electric aircraft, a sensor coupled to the battery pack and configured to detect a battery pack output, and a computing device coupled to the sensor. The computing device is configured to receive the battery pack output from the sensor and adjust a maximum speed of the electric aircraft as a function of the battery pack output and a battery pack output threshold.

Abstract: A system for monitoring sensor reliability in an electric aircraft is provided. The system includes a computing device communicatively connected to a first sensor and an electric aircraft. The first sensor is mechanically connected to the electric aircraft and is configured to detect a first flight datum of the electric aircraft. The computing device is configured to receive the first flight datum from the first sensor, compare the first flight datum to at least a corroboratory datum, and tag the first sensor as a function of the comparison of the first flight datum and the at least a corroboratory datum. A method for monitoring sensor reliability in an electric aircraft is also provided.

Abstract: A hybrid electric vertical takeoff and landing (VTOL) aircraft. The hybrid electric VTOL aircraft generally includes a fuselage, a pair of wings, a pair of booms, a plurality of flight components and a power system. The wings are connected to the fuselage and extend generally laterally therefrom with each wing on either side of the fuselage. Each boom is connected to a respective one of the wings and extends generally longitudinally and parallel to the fuselage. The plurality of flight components is configured to provide thrust to the hybrid electric VTOL aircraft. The power system is configured to power the plurality of flight components and includes at least a fuel tank and a generator, and at least a battery. The at least a fuel tank is mounted to at least one of the booms. The at least a battery configured to power the plurality of flight components.

Abstract: A fuel-based flight indicator apparatus for an electric aircraft is illustrated. The apparatus comprises a flight indicator and a computing device communicatively connected to the flight indicator, wherein the computing device is configured to receive a battery datum from a battery sensor located in the electric aircraft, receive an environmental datum from an environmental sensor located in the electric aircraft, determine an indicator datum as a function of the battery datum, the environmental datum, and a flight plan, and display the indicator datum on the flight indicator.