Abstract: An assembly and a method of manufacturing a battery pack with airgap sizing for preventing ejecta debris clogging for an electric aircraft are disclosed. The assembly includes a battery module configured to house a battery unit, wherein the battery module includes a battery cell and a cooling plate configured to stabilize battery cell temperature. The assembly includes a fire wall configured to intercept ejecta debris from the battery cell. The assembly includes an airgap configured to contain the ejecta debris between the firewall and the battery cell. The assembly includes a headspace configured to tolerate the ejecta debris on top of the battery cell, wherein the headspace includes an ejecta vent configured to vent the ejecta debris.

Abstract: A system and method for using unrecoverable energy in a battery cell is disclosed in this application. A system includes a battery cell, the battery cell includes an excess amount of cathode or anode that can function as half cells in an emergency. A user, such as a pilot, can command a controller to utilize unrecoverable energy based on battery data presented to the user.

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: Disclosed herein are systems and methods for propulsor cyclic control. Propulsor cyclic control may be used to reduce asymmetric loads in aircraft flight. A system for propulsor cyclic control may include an electric aircraft comprising a motor, a propulsor, and a cyclic. Cyclic may be controlled passively or actively.

Abstract: Systems and methods for reducing common mode failures in flight control of an aircraft is disclosed herein. Reducing common mode failures includes using dissimilar components. Dissimilar components found in flight control of an aircraft may include sensors, effectors, command processors, and monitor processors. One or more flight controllers are used to transmit commands to effectors and monitor effectors using dissimilar sensors.

Abstract: An apparatus and method for calculating anticipated energy consumption for electric aircraft are disclosed. The method may include receiving flight plan data and determining at least a flight phase as a function of the flight plan data. Further, the method may include estimating a duration and energy consumption rate for the at least a flight phase, estimating a usable energy capacity of the electric aircraft, and determining a value of additional energy to add to the electric aircraft.

Abstract: An apparatus for an inertial separation of air in an electric aircraft, wherein the apparatus includes an intake duct configured to intake an airflow, an inertial air separator configured to separate the airflow into a clean airflow and a dirty airflow, a propulsor configured to intake the clean airflow, wherein the propulsor includes a stator and a rotor, and a heat exchanger configured to intake the dirty airflow.

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 environment management in an electric aircraft, where in the system include, at least a at least a battery pack mounted within a fuselage of an electric aircraft. A battery pack may include a plurality of batteries configured to provide electrical power to the electric aircraft. A battery pack may also include a pouch cell. Adjacent to the battery pack there may be at least a channel. A channel is configured to provide a flow path for directing battery ejecta to a predetermined location.

Abstract: Disclosed herein is a system and method for effector reboot on an electric aircraft during flight. An effector controller may perform a power on built-in test on boot. An effector controller may selective perform an additional built-in test (ABIT) on boot based on instructions from a flight controller. The flight controller may use flags to indicate the necessity of an ABIT on boot. The effector controller may not perform an ABIT during flight. A backup controller may be used to send standard commands to an effector controller but may not sent an ABIT command.

Abstract: In an aspect a system for electric charger communication is presented. A system includes a first networking component and sensor of a first electric charger. The system includes at least a processor communicatively connected to a first networking component and the sensor. The system includes memory communicatively connected to at least a processor, wherein the memory contains instructions configuring at least a processor to receive the at least a charger metric from the sensor and transmit the at least a charger metric to the network using the first communicative connection, wherein the at least a charger metric comprises a charger status.

Abstract: This application discloses an apparatus and method for displaying pilot control authority. This apparatus and method include using a controller to identify a condition of an aircraft and determine a limitation in pilot control authority. Using this, an indicator on a display may show a visual representation of a pilot control authority, the limitations thereof, and a pilot input.

Abstract: Aspects of the present disclosure include an aircraft with auxiliary components that are powered by an external power supply. Auxiliary components may include components that are used while the aircraft is grounded. Auxiliary components may be off while the aircraft is in flight.

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 include a vent port connected to a venting path to an outlet used to vent battery ejecta in thermal runaway events. The apparatus is designed to prevent ejecta from passing beneath an electrochemical cell.

Abstract: In an aspect of the present disclosure is an electric aircraft motor with a fully welded rotor. The motor includes a stator and a rotor. The stator includes an inner cylindrical surface and an outer cylindrical surface. The rotor includes a cylindrical portion and spokes welded to the cylindrical portion. In another aspect of the present disclosure is a method for manufacturing a fully welded rotor.

Abstract: A rotor for a motor of an electric aircraft is provided. The rotor includes a retention band surrounding a plurality of magnets. The retention band is designed to retain the magnets in their positions and provide a way for heat to dissipate from the magnets. The retention band may also reduce eddy currents found within the rotor. A method of manufacturing a rotor with a retention band is also provided.

Abstract: Aspects of the present disclosure include an aircraft with auxiliary components that are powered by an external power supply. Auxiliary components may include components that are used while the aircraft is grounded. Auxiliary components may be off while the aircraft is in flight.

Abstract: Various techniques are provided to assemble, manufacture, and use a power source. A power source assembly system is provided to apply a compressive force on a plurality of battery cells so that the battery cells may be inserted into a compact container without damaging the battery cells.

Abstract: An apparatus for manufacturing a stator for an electric aircraft motor, wherein the apparatus includes at least a manufacturing device. The manufacturing device further includes at least a work-holding device configured to hold a first segment of teeth. The manufacturing device further includes at least a winding device configured to create a modular winding set in the first segment of teeth, wherein creating a modular winding set further include acquiring a continuous conductor and winding a continuous conducting coil upon each tooth of the plurality of teeth using the continuous conductor. The manufacturing device further includes at least an installation device configured to install a plurality of segment of teeth into the stator.

Abstract: A system and a method for a battery power management system for an electric aircraft is disclosed. The system includes at least a flight component of an electric aircraft, at least a battery, wherein the at least a battery is configured power the at least a flight component of the electric aircraft, at least a sensor communicatively connected to the at least a battery and a controller communicatively connected to the at least a sensor. The controller is configured to receive sensor data from the at least a sensor, identify a battery status as a function of the sensor data and a battery threshold, and control the power from the at least a battery to the at least a flight component of the electric aircraft as a function of the battery status, further comprising reducing a torque to the at least a flight component.