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: 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: 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 electricity to the centralized electrical bus, wherein the plurality of modular battery packs is arranged about a center of gravity of the electric aircraft.

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: An apparatus for a locking thermal conditioning hose for an electric aircraft, the apparatus comprising a thermal conditioning hose comprising a thermal medium flow path configured to contain a flow of a thermal medium, a thermal medium return path, the thermal medium return path configured to contain a flow of the thermal medium from an electric aircraft, and a mating component, wherein the mating component is configured to make a connection with an electric aircraft port, and a thermal latch, wherein the thermal latch is configured to couple the thermal conditioning hose to the electric aircraft.

Abstract: A stator with cooling system for an electric motor of an electric aircraft and a method of manufacturing a stator of an electric motor for an electric aircraft with cooling system are disclosed. The stator may include a winding configured to provide magnetic flux and comprising an electrically conductive material. The stator may further include a soft magnet configured to hold the winding. The stator may further include a passive heat sink in thermal communication with the winding and comprising a phase change material.

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: 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 method of in-flight operational assessment for an electric aircraft comprising detecting by a sensor an electrical parameter of an energy source. The method further includes receiving by a controller the electrical parameter from the sensor and determining a power-production capability of the energy source, using the electrical parameter. The method further includes calculating, by the controller, a projected power-consumption need of the electric aircraft and comparing the determined power-production capability of the energy source to the projected power-consumption need. The method includes generating a power production command datum as a function of the comparison of the power-production capability and the projected power-consumption need.

Abstract: A method for the manufacturing of battery packs includes vertically stacking a plurality of battery cells to create a stack of battery cells, applying a compressive force on the stack of battery cells using a plurality of pneumatic cylinders, inserting a first portion of the compressed stack of battery cells into a container prior to releasing any of the plurality of pneumatic cylinders, engaging each of the battery cells of the plurality of battery cells with an end cap of the container, wherein the end cap is configured to maintain a predetermined arrangement of the plurality of battery cells, and releasing the first portion of the stack of battery cells from a first portion of the plurality of pneumatic cylinders while a second portion of the stack of battery cells remains compressed a second portion of the plurality of pneumatic cylinders.

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 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: 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: 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: 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: 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: 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: 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.