Abstract: An aircraft having reverse thrust capabilities includes a fuselage, a plurality of flight components, a pilot control located within the fuselage, a sensor attached to the pilot control configured to detect an aircraft datum from the pilot control, and a flight controller, located within the fuselage, the flight controller configured to receive the aircraft datum from the sensor, and initiate a reverse torque command of a flight component of the plurality of flight components as a function of the aircraft datum.

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 venting assembly for battery ejecta opposite an egress, wherein the venting assembly comprises a plurality of battery packs configured to power the electric aircraft, a plurality of vents wherein each vent of the plurality of vents is attached to each battery pack of the plurality of battery packs, and at least an outlet in fluidic communication with the plurality of vents, wherein the at least an outlet is located on an opposite side of the electric aircraft as an egress.

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: 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: An aircraft having reverse thrust capabilities includes a fuselage, a plurality of flight components, a pilot control located within the fuselage, a sensor attached to the pilot control configured to detect an aircraft datum from the pilot control, and a flight controller, located within the fuselage, the flight controller configured to receive the aircraft datum from the sensor, and initiate a reverse torque command of a flight component of the plurality of flight components as a function of the aircraft datum.