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 for disconnecting a battery from an electric aircraft upon impact. The system includes an electric aircraft and a battery assembly electrically coupled to the electric aircraft. The battery assembly is configured to include at least a sensor. The at least a sensor is configured to detect impacts to the electric aircraft. The battery assembly is configured to include a connector. The connector attaches the battery assembly to the electric aircraft. The connector includes an electrically actuating disconnection mechanism. The battery assembly is configured to include a control circuit. The control circuit is electrically connected to the electrically actuating disconnection mechanism. The control circuit is configured to detect, using the at least a sensor, an impact to the aircraft. The control sensor disconnects the connector from the electric aircraft using the electrically actuating disconnection mechanism as a function of the detection of impacts to the electric aircraft.

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, 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 of the present disclosure is a system for locking a battery for an electric aircraft, the system including a battery pack including a high voltage (HV) connection configured to electrically connect to the electric aircraft; and a lock attached to the battery pack and configured to electrically disconnect the battery pack from the electric aircraft when locked, wherein the lock is configured to only be unlocked manually.

Abstract: In an aspect of the present disclosure is a system for locking a battery for an electric aircraft, the system including a battery pack including a high voltage (HV) connection configured to electrically connect to the electric aircraft; and a lock attached to the battery pack and configured to electrically disconnect the battery pack from the electric aircraft when locked, wherein the lock is configured to only be unlocked manually.

Abstract: Certain aspects relate to a battery pack for an electric vehicle. Exemplary battery pack includes a first pouch cell and a vent configured to vent the ejecta from the first pouch cell. The first pouch cell includes at least an outer coating, at least a first pair of electrodes, at least a first pair of foil tabs electrically connected to the at least a first pair of electrodes, at least a first insulator layer located substantially between the at least a first pair of foil tabs, a first pouch substantially encompassing the at least a first pair of foil tabs and the at least a first insulator layer, and a first electrolyte within the first pouch. The battery pack is also configured to power at least a propulsor component.

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: Certain aspects relate to a battery pack for electric vertical take-off and landing aircraft. Exemplary battery pack includes a first pouch cell, a second pouch cell, at least a sensor, where the at least a sensor is configured to sense battery pack data and transmit the battery pack data to a data storage system, and a vent configured to vent the ejecta from the first pouch cell. In some embodiments, battery pack may be configured to power at least a propulsor component.

Abstract: A system for disconnecting a battery from an electric aircraft upon impact. The system includes an electric aircraft and a battery assembly electrically coupled to the electric aircraft. The battery assembly is configured to include at least a sensor. The at least a sensor is configured to detect impacts to the electric aircraft. The battery assembly is configured to include a connector. The connector attaches the battery assembly to the electric aircraft. The connector includes an electrically actuating disconnection mechanism. The battery assembly is configured to include a control circuit. The control circuit is electrically connected to the electrically actuating disconnection mechanism. The control circuit is configured to detect, using the at least a sensor, an impact to the aircraft. The control sensor disconnects the connector from the electric aircraft using the electrically actuating disconnection mechanism as a function of the detection of impacts to the electric aircraft.

Abstract: A system for a pouch cell casing configured for use in an electric aircraft includes at least a pouch cell. The at least a pouch cell includes at least a pair of cell tabs, a battery cell, a pouch substantially encompassing the battery cell and the at least a pair of cell tabs. The at least a pouch cell includes at least a first side, a cell casing configured to substantially encompass the at least a pouch cell and including a first face disposed parallel and adjacent to the at least a first side, a second face disposed perpendicular and affixed to the first face, and at least an opening disposed on the first face opposite and adjacent to the at least a first side.

Abstract: Certain aspects relate to a battery pack for electric vertical take-off and landing aircraft. Exemplary battery pack includes a first pouch cell, a second pouch cell, at least a sensor, where the at least a sensor is configured to sense battery pack data and transmit the battery pack data to a data storage system, and a vent configured to vent the ejecta from the first pouch cell. In some embodiments, battery pack may be configured to power at least a propulsor component.

Abstract: A system and method for a thermal management system for a plurality of battery cells.

Abstract: A system and method for management of a battery pack for an electric aircraft.

Abstract: A battery management system integrated in a battery pack configured for use in electric aircraft, the system comprising a first battery management component disposed on a first end of the battery pack, the first battery management component comprising a first sensor suite configured to measure a first plurality of battery pack data wherein the first sensor suite comprises a moisture sensor. The battery management system comprising a second battery management component disposed on a second end of the battery pack, the second battery management component comprising a second sensor suite configured to measure a second plurality of battery pack data wherein the second sensor suite comprises a moisture sensor. The battery management system comprising a data storage system configured to store the first plurality of battery pack data and the second plurality of battery pack data.

Abstract: A battery management system integrated in a battery pack configured for use in electric aircraft, the system comprising a first battery management component disposed on a first end of the battery pack, the first battery management component comprising a first sensor suite configured to measure a first plurality of battery pack data wherein the first sensor suite comprises a moisture sensor. The battery management system comprising a second battery management component disposed on a second end of the battery pack, the second battery management component comprising a second sensor suite configured to measure a second plurality of battery pack data wherein the second sensor suite comprises a moisture sensor. The battery management system comprising a data storage system configured to store the first plurality of battery pack data and the second plurality of battery pack data.