Abstract: A distributed control system with supplemental attitude adjustment including an aircraft control having an engaged state and a disengaged state. The system also including a plurality of flight components and a plurality of aircraft components communicatively connected to the plurality of flight components, wherein each aircraft component is configured to receive an aircraft command and generate a response command directing the flight components as a function of supplemental attitude. The supplemental attitude based at least in part on the engagement datum and generating a supplemental attitude includes choosing a position supplemental attitude if the aircraft control is disengaged and choosing a velocity supplemental attitude if the aircraft control is engaged. In generating the response command, the aircraft attitude is combined with the supplemental attitude to obtain an aggregate attitude, and the aircraft component is configured to generate the response command based on the aggregate attitude.

Abstract: In an aspect, a system for displaying synoptic information is provided. A processor of the system may retrieve and/or receive operation data related to the use of a corresponding electric aircraft. Operation data may be displayed on a display of the system using one or more visual representations or audio presentations.

Abstract: In an aspect, this disclosure is related to apparatus and method for optimizing motor performance in an electric vertical takeoff and landing aircraft. Apparatus includes a motor, an inverter, a sensor, and a flight controller. Flight controller is configured to receive an operational datum from a sensor, which detects a physical phenomenon and generates an operational datum. Flight controller is configured to generate an optimized switching frequency for the inverter based on the operational datum. Flight controller is configured to adjust the switching frequency of the inverter based on the optimized switching frequency.

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: A system for managing residual energy for an electric aircraft, wherein the system includes a battery pack incorporated in the electric aircraft, wherein the battery pack includes a plurality of battery modules and at least a pack monitor unit configured to generate a battery pack datum. The system further includes a charging component connected to the battery pack and a sensor connected to the charging component and configured to detect at least an electrical parameter of the charging component and the electric aircraft and generate a residual datum as a function of the at least an electrical parameter and the battery pack datum. The system further includes a computing device configured to receive the residual datum from the sensor, identify a residual element, generate an alert datum as a function of the residual element, and execute a security measure as a function of the alert datum.

Abstract: An apparatus for determining a resource remaining datum of an electric aircraft is disclosed. The apparatus includes a processor and a memory communicatively connected to the processor. The memory contains instructions configuring the processor to receive aircraft data from at least a sensing device, wherein the at least a sensing device is configured to measure at least a parameter of a battery pack of the electric aircraft and generate aircraft data as a function of the at least a parameter of the battery pack of the electric aircraft. The memory contains instructions configuring the processor to determine a reserve energy as a function of a flight mode of the electric aircraft and determine a resource remaining datum as a function of the aircraft data and the reserve energy, wherein the resource remaining datum is related to the battery pack of the electric aircraft.

Abstract: In an aspect, a system for monitoring a battery system in-flight. The system includes at least a battery pack and a pack monitoring unit (PMU) communicatively connected with a battery pack. The battery pack includes a plurality of battery packs. The PMU may include at least a sensor and a controller. At least a sensor is configured to detect battery datum. A controller is communicatively connected with at least a sensor. A controller is configured to receive battery datum, detect a significant event as a function of battery datum, and transmit the significant event to a remote device.

Abstract: A system and method for pilot assistance in an electric vertical takeoff and landing (eVTOL) aircraft. The system generally includes a pilot control and a flight controller. The pilot control is attached to the eVTOL aircraft. The pilot control is configured to transmit an input relating to the flight path of the aircraft. The flight controller is communicatively connected to the pilot control. The flight controller is configured to receive the input relating to the flight path, generate an output of a recommended flight maneuver as a function of the input, and display the recommended flight maneuver.

Abstract: A system for determining remaining useful energy in an electric aircraft, the system including a computing device where the computing device is configured to measure a internal state datum of a battery as a function of at least a sensor, receive the internal state datum from the at least a sensor, generate a useful energy remaining datum as a function of the internal state datum and a battery model, and display the useful energy remaining datum to a user.

Abstract: The present invention is directed to systems and methods for managing thermal energy of an electric vertical takeoff and landing aircraft. The system comprises of a multilayer laminate that includes a rigid layer and an insulation layer. The multilayer laminate may be laid on a structural element of an aircraft. The aircraft comprises an active component.

Abstract: In an aspect, an assembly for gauging fuel of an electric aircraft is presented. A assembly includes a plurality of battery packs of an electric aircraft. Each battery pack of a plurality of battery packs includes a plurality of battery modules. An assembly include at least a battery sensor in electronic communication with a battery pack of a plurality of battery packs. At least a battery sensor is configured to measure battery data. An assembly includes a computing device communicatively connected to at least a battery sensor. A computing device is configured to receive battery data from at least a battery sensor. A computing device is configured to determine a landing energy as a function of battery data. A computing device is configured to provide landing energy to a user through a display.

Abstract: An electric vertical takeoff and landing aircraft including a teetering propulsor assembly is provided. Teetering propulsor assembly may include a propeller that includes a hub and blades. Hub of propeller may be mechanically connected to a teeter mechanism of propulsor assembly that may be configured to allow the propeller to pivot about a teeter axis relative to the electric aircraft. Thus, teeter mechanism allows for a rotational axis of propeller to move during teetering of propeller. Teeter mechanism may include one or more springs that reduce teetering or prevent teetering of the propulsor at certain rotational speeds of propeller.

Abstract: In an aspect, a propulsor gauge is provide that provides guidance during a transition of a mode of operation of an electric aircraft. Propulsor gauge may include a processor configured to identify a current thrust envelope parameter of one or more propulsors of electric aircraft. Processor may also determine a recommended range as a function of the propulsor parameter, where the recommended range includes a lower threshold and an upper threshold. The recommended range and thrust envelope parameter may then be shown on a display of propulsor gauge, where a measurement of current thrust envelope parameter relative to recommended range may be represented by an indicator.

Abstract: The present invention is systems and methods for preflight temperature management of an energy source of an electric aircraft. The system may include a sensor attached to an energy source of an electric aircraft, where the sensor is configured to detect a temperature of the energy source and generate a corresponding temperature datum. A computing device communicatively connected to the sensor may receive the temperature datum and determine the readiness of the electric aircraft for flight based on the temperature of the energy source. If the electric aircraft is not considered ready by the computing device, then an energy source modification may be initiated that changes the temperature of the energy source.

Abstract: A system for charger management for electrical vertical takeoff and landing aircrafts includes a sensor connected to the first charger. The sensor is configured to detect a battery metric and transmit the metric to a computing device. The computing device is connected to a mesh network. The mesh network contains many aircrafts connected to chargers. The charger management system manages the charging of the aircraft.

Abstract: The system and method for defining boundaries of a simulation of an electric aircraft is illustrated. The system comprises a sensor, a computing device, and a remote device. The sensor is configured to detect an aircraft location datum, detect a boundary datum associated with a three-dimensional flying space, and transmit the aircraft location datum and boundary datum to a computing device. The computing device is configured to receive the aircraft location datum and boundary datum from the sensor, determine a distance datum between the aircraft location and boundary as a function of the aircraft location datum and boundary datum generate a recommended aircraft adjustment as a function of the distance datum, and transmit the distance datum and recommended aircraft adjustment to a remote device. The remote device is configured to receive the distance datum and recommended aircraft adjustment and display them to a user.

Abstract: An electric vehicle charging connector including a charging connector. The charging connector including a direct current pin and an alternating current pin. The electric vehicle charging connector also including a coupling mechanism configured to: couple the charging connector to an electric vehicle, enable a flow of electricity from the charging connector to the electric vehicle, and disable the flow of electricity from the charging connector to the electric vehicle.

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: Aspects relate to a connector for charging an electric vehicle and a method for its use. An exemplary connector includes at least a direct current conductor configured to conduct a direct current, at least an alternating current conductor, configured to conduct an alternating current, at least a computing device wherein the computer is configured to receive a measurement datum of a battery module from a communicatively connected sensor, determine an operating condition of the charging circuit; identify an error element as a function of the operating condition, and transmit the identification of the error element to a data storage system.