Abstract: 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.

Abstract: Aspects relate to method and systems for wrapping simulated intra-aircraft communication to a physical controller area network. An exemplary method includes receiving simulator data from an aircraft simulator, disaggregating a simulated digital message from the simulator data, abstracting a simulated signal as a function of the simulated digital message, transmitting the simulated signal on at least a controller area network (CAN), receiving, using at least an aircraft component communicative with the at least a CAN, the simulated signal by way of the at least a CAN, transmitting a phenomenal signal by way of the at least a CAN, receiving the phenomenal signal by way of the at least a CAN, converting a phenomenal digital message as a function of the phenomenal signal, and inputting the phenomenal digital message to the aircraft simulator.

Abstract: An aircraft monitoring system for an electric aircraft is disclosed. The monitoring system may include at least a sensor configured to generate a failure datum. The failure datum includes a datum regarding a condition of an electric motors. An electronic checklist may include a crew alerting system (CAS). A CAS may be in electronic communication a sensor, wherein the CAS is comprised of at least a computing device. A CAS may generate a plurality of remedy data as a function of the failure datum. A CAS then may display the plurality of remedy data using a pilot display. A pilot may be prompted to apply the remedy datum using a pilot display as a function of the plurality of remedy data. The CAS provides an indication of the condition of the electric motor using a pilot display as a function of the application of the plurality of remedy data.

Abstract: Provided in this disclosure is a battery module with a cooling plate and a firewall. Battery modules may include a firewall located proximal to the plurality of battery cells and configured to absorb heat from the battery cells. Firewall may include a stack of materials. Battery module may include a cooling plate between rows of battery cells configured to cool the battery cells.

Abstract: In an aspect the current disclosure is directed to an electric vehicle charger for an electric vehicle. The electric vehicle charger is comprised of an energy source, a transmitter coil electrically connected to the energy source and configured to wirelessly conduct a current in a receiver coil using induction, at least a proximity sensor configured to generate alignment data relating to an electric vehicle, and a computing device that is communicatively connected to the at least a proximity sensor. The computing device may be configured to identify the electric vehicle. Identification may include receiving and authenticating at least an identification datum, and identifying the electric vehicle using that; The computing device is configured to align the transmitter coil with the receiver coil using the alignment data. Additionally, the computing device may be configured to authorize the electric vehicle to be begin charging as a function of the authentication.

Abstract: A system and method for the overcurrent protection in an electric vehicle is illustrated. The system comprises an electric vehicle charging port that includes an AC pin, a DC pin, a sensor, and a controller. The electric vehicle charging port also includes a protection circuit, wherein the protection circuit is configured to control a transmission of power through the electric vehicle charging port.

Abstract: Aspects relate to an electric vehicle port and methods of use for charging an electric vehicle. An exemplary electric vehicle port includes a housing configured to mate with a connector for charging an electric vehicle, wherein the housing comprises a fastener for removable attachment with the connector; at least a conductor configured to conduct a current; at least a control signal conductor configured to conduct a control signal; at least a ground conductor configured to conduct to a ground; and at least a coolant flow path configured to contain a flow of a coolant, wherein, each of the at least a conductor, the at least a control signal conductor, the at least a ground conductor, and the at least a coolant flow path are configured to make a connection with a mating component on the connector for charging the electric vehicle when the housing is mated with the connector.

Abstract: An apparatus for venting battery ejecta for use in an electric aircraft is presented. The apparatus includes a battery module with a plurality of electrochemical cells. The electrochemical cells of the plurality of electrochemical cells are separated by a carbon fiber barrier. Venting port of a plurality of venting ports is configured to vent an electrochemical cell of the plurality of electrochemical cells using a venting path of a plurality of venting paths, wherein the plurality of vent ports is fluidly connected to the plurality of venting paths and the plurality of venting paths are fluidly connected to at least an outlet. Venting paths direct the battery ejecta from the electrochemical cell to the outside of the electric aircraft through at least an outlet.

Abstract: A system for fault detection and control in an electric aircraft including an inertial measurement unit, the inertial measurement unit including at least a sensor configured to detect a torque datum associated with at least a propulsor. The system includes an observer, the observer configured to generate a torque prediction datum associated with the at least a propulsor, compare the torque prediction datum with the torque datum, and generate a residual datum as a function of the comparison. The system includes a mixer, the mixer comprising circuitry configured to generate, as a function of the residual datum, a torque priority command datum and transmit, to the at least a propulsor, the torque priority command datum.

Abstract: A combined cyclic and teeter system for an electric vertical takeoff and landing (eVTOL) aircraft is disclosed. In some embodiments, the eVTOL aircraft may include a motor and a propulsor driven by the motor, wherein the propulsor may include a propeller with a rigid blade and configured to propel the eVTOL aircraft. In some embodiments, the eVTOL aircraft may include a cyclic attached to the propeller and configured to change a pitch of blades of the propeller. In some embodiments, the eVTOL aircraft may include a passive flap attached to the propeller and configured to passively control flight transients, wherein the passive flap may include a base rotatably affixed to the propulsor and configured to rotate about a rotational axis and a hinge connecting the base and the propeller and configured to allow the propeller to pivot about a pivot point of the hinge.

Abstract: A system for estimating percentage torque produced by a propulsor configured for use in an electric aircraft, the system including a propulsor, the propulsor configured to generate output torque. The system including a sensor, the sensor configured to detect the output torque and generate an output torque datum. The system including a flight controller including a computing device configured to receive an output torque datum, receive an ideal propulsor model, the ideal propulsor model including at least a performance parameter, generate a model torque datum, including a model torque datum threshold, as a function of the at least a performance parameter, generate a percentage datum as a function of the output torque datum and model torque datum, and determine, at least an obstruction datum correlated to the torque percentage datum, and display torque percentage datum and the at least an obstruction datum.

Abstract: A system and method for storing aircraft component information on an immutable sequential listing, wherein the system comprises a computing device configured to identify a plurality of aircraft components, assign a component identifier to each aircraft component of a plurality of aircraft components, generate, for each component identifier, an immutable sequence entry including the component identifier, and store, for each component identifier, the corresponding immutable sequence entry on at least an immutable sequential listing.

Abstract: A system of pay-in and pay-out function of a cooling system for an electric vehicle and a method of use is presented in this disclosure. The system may include a cooling cable, a cooling connector, wherein the cooling connector may include an actuator, a cable reel, and an idler drum. The cable reel may include a helical pattern where the cooling cable resides during the stowed configuration. The idler drum may be parallel to the cable reel.

Abstract: An apparatus for pre-flight preparation for an electric aircraft including at least a processor and memory communicatively connected to the processor. The memory containing instructions configuring the at least a processor to generate a plurality of aircraft conditioning data using at least a sensor. The memory containing instructions further configuring the processor to engage at least an aircraft conditioning system using power from an auxiliary power supply, The aircraft conditioning system is configured to receive the plurality of aircraft conditioning data from the at least a sensor, test the output of the at least a sensor against an expected value of the at least a sensor, and initiate the aircraft conditioning system as a function of the aircraft conditioning data.

Abstract: A system for autonomous flight of an electric vertical takeoff and landing (eVTOL) aircraft. The system may include a pusher component, a lift component, a flight controller, and a pilot override switch. The pusher component is mechanically coupled to the eVTOL aircraft. The lift component is mechanically coupled to the eVTOL aircraft. The flight controller is communicatively connected to the pilot override switch. The flight controller is configured to identify a transition point, initiate operation of the pusher component, and terminate operation of the lift component. A method for flight control of an eVTOL aircraft is also provided.

Abstract: In an aspect, a modular battery configuration with a centralized bus on an electric aircraft, including an electric aircraft which comprises a propulsor configured to generate thrust and a centralized electrical bus connected to the propulsor. A plurality of modular battery packs is configured to provide electricy to the centralized electrical bus, wherein the plurality of modular battery packs is arranged about a center of gravity of the electric aircraft.

Abstract: A system for redistributing electrical load in an electric aircraft. The system includes a ring bus and a controller communicatively connected to the ring bus. The ring bus includes a plurality of bus sections including a first bus section and a second bus section. The controller is configured to receive a fault datum indicative of a fault associated with one of a first energy source and a second energy source, actuate, as a function of the fault datum, at least a switch to electrically connect the first bus section and the second bus section so as to form an electrical merger of the first bus section and the second bus section, and redistribute the electrical load to compensate for the fault associated with one of the first energy source and the second energy source. A method of redistributing electrical load in an electric aircraft is also provided.

Abstract: A battery management system includes a low-power chip that allows battery management system, or components thereof, to alternate between operational states. Operational states may include a first state, a second state, a third state, and the like.

Abstract: An electric vehicle charger for an electric vehicle is provided. The electric vehicle charger includes a charging cable and a charging connector mechanically connected to the charging cable. The charging connector includes a rotation mechanism that may control a “pay in” and a “pay out” function of the electric vehicle charger, a cable reel configured to stow the charging cable, and a first idler drum associated with the cable reel. The first idler drum may produce a resultant force during the “pay out” function, thereby pushing the charging cable away from the cable reel. The rotation mechanism may include a rotary actuator mechanically connected to the cable reel. The rotary actuator may rotate the cable reel and produce the resultant force during the “pay out” function.