Abstract: An apparatus for a ground-based battery management for an electric aircraft is presented. The apparatus includes a battery pack mechanically coupled to the electric aircraft, the battery pack includes at least a battery module that includes at least a battery unit that includes battery cells and a thermal conduit configured to transfer heat between the battery cells and the thermal conduit and a thermal circuit mechanically coupled to the thermal conduit configured to facilitate the heat transfer using thermal media. The apparatus includes a media channel communicatively connected to a computing device and comprising at least a sensor, wherein the media channel is configured to evacuate the thermal media out of the battery pack using the thermal circuit and the computing device that includes a battery management system is configured to receive a condition parameter as a function of the at least a sensor of the media channel.

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 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.

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: A battery venting system having a battery module containing a plurality of pouch cells. The battery module also includes a vent port. The battery venting system also including a vent outlet disposed on the surface of an aircraft fuselage. The battery venting system further including a vent conduit fluidly connecting the vent port of the battery module to the vent outlet. The vent conduit is configured to carry battery ejecta from the battery module, from the vent port to the vent outlet. The vent conduit includes at least a cooling fin disposed on an interior wall of the vent conduit and extending into the vent conduit, the at least a cooling fin configured to dissipate heat from the battery ejecta, when the battery ejecta is in the vent conduit.

Abstract: A system for a venting seal for battery modules in an electric aircraft is presented. The system includes a plurality of battery modules, wherein each battery module comprises a vent conduit, a contactor configured to disengage at least a catalyst battery module as a function of a thermal event, and an electrical bridging device configured to seal off the at least a catalyst battery module as a function of an independent seal, disengage the at least a catalyst battery module from the remaining plurality of battery modules, and transfer electrical energy across the plurality of battery modules.

Abstract: A method for a venting seal for battery modules in an electric aircraft is presented. The method includes sealing off, by an independent seal, a battery module of a plurality of battery modules from a vent conduit during typical operation, unsealing, by independent seal, the vent conduit as a function of a thermal event, disengaging, by a contactor of an electrical bridging device, at least a catalyst battery module from the remaining plurality of battery modules, and transferring, by the electrical bridging device, electrical energy across the remaining plurality of battery modules.

Abstract: In an aspect, a system for battery temperature management in an electric aircraft. In some embodiments, the system includes a plurality of battery cells, comprised of pouch cells. The system includes at least a sensor communicatively connected to a computing device. At least a sensor may be configured to detect temperature. A system also includes a plurality of temperature regulating elements disposed between the plurality of pouch cells. A temperature regulating elements are configured to maintain the temperature of the battery pack. The system also includes a computing device communicatively connected to the plurality of temperature regulating elements. A computing device is configured to determine a target temperature of the plurality of cells and direct the plurality of temperature regulating elements to modify a temperature of the plurality of battery cells as a function of the target temperature.

Abstract: A battery pack for an electric aircraft is disclosed. The battery pack may include a pouch cell within a sealed environment, wherein the pouch cell may include a pair of electrodes, wherein the pair of electrodes is configured to carry electrical current. The pouch cell may include an insulator layer, the insulator layer located between the pair of electrodes. The pouch cell may include an electrolyte within the pouch cell. The pouch cell may include a pouch, the pouch substantially surrounding the pair of electrodes, the electrolyte and the insulator layer. The pouch cell may include a pair of foil tabs in electrical communication with the pair of electrodes and emanating from the sealed environment. The pouch cell may include a seal, wherein the seal is configured to seal about the pair of foil tabs and prevent a flow of cell ejecta from a thermal runaway.

Abstract: A battery pack assembly for use in an aircraft is disclosed. The battery pack assembly may include at least a battery cell, wherein the battery cell may include a pair of electrodes, a pair of conductive foil tabs and an electrolyte. The battery pack assembly may include a battery cell case, wherein the battery cell case is configured to surround at least a portion of the at least a battery cell, wherein the battery cell case may include a layer, wherein the layer is configured to provide a pressure against the at least a battery cell.

Abstract: Aspects relate to systems methods for battery management in an electric aircraft. An exemplary system includes a propulsor configured to generate thrust on the electric aircraft, an electric motor configured to power the propulsor, a battery pack configured to provide electrical energy to the electric motor, wherein the battery pack includes a plurality of battery cells, a conductor configured to provide electrical communication to the plurality of battery cells, and a contactor configured to selectably disengage electrical communication within the conductor, a gas sensor configured to detect a gas parameter associated with the battery pack, and a computing device configured to receive the gas parameter from the gas sensor, determine a battery condition associated with the battery pack, and controlling the contactor to disengage the electrical communication within the conductor as a function of the battery condition.

Abstract: In an aspect, a system for battery ventilation of an electric aircraft. A system includes an electric aircraft. An electric aircraft includes a plurality of battery cells. Each battery cell of the plurality of battery cells includes a battery tab. A system includes a sensor in electronic communication with a plurality of battery cells. A sensor is configured to measure battery cell data. A system includes a plurality of vents. Each vent of the plurality of vents is positioned by each battery tab of the plurality of battery cells. A system includes a flight controller. A flight controller is configured to receive battery cell data from a sensor. A flight controller is configured to determine a vent arrangement as a function of battery cell data. A flight controller is configured to position at least a vent of a plurality of vents as a function of a vent arrangement.

Abstract: A heat-dissipating battery pack is disclosed. The heat-dissipating battery pack may include at least a pouch battery cell. The at least a pouch battery cell may include a pair of electrodes. The at least a pouch battery cell may include a pouch, wherein the pouch substantially surround the pair of electrodes. The at least a pouch battery cell may include an electrolyte within the pouch. The at least a pouch battery cell may include a vent of the at least a pouch battery cell, wherein the vent of the at least a pouch battery cell is configured to discharge battery ejecta ejected during a thermal runaway as a function of temperature and pressure.

Abstract: An apparatus for a ground-based battery management for an electric aircraft is presented. The apparatus includes a battery pack mechanically coupled to the electric aircraft, wherein the battery pack includes at least a battery module, wherein each battery module includes at least a battery unit containing a first row of battery cells, a second row of battery cells, and a thermal conduit disposed between the first row and the second row of the battery unit, wherein the thermal conduit is configured to precondition the battery cells. Each battery module includes a thermal circuit mechanically coupled to the thermal conduit configured to facilitate the precondition using thermal media. The apparatus further includes a media channel encompassing the battery pack configured to connect to a ground cooling component that provides the thermal media to the thermal circuit using the thermal circuit, and evacuate the thermal media using the thermal circuit.

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 stack battery pack for an electric vertical take-off and landing aircraft includes a first pouch cell comprising a first top surface and a first bottom surface, a second pouch cell comprising a second top surface and a second bottom, wherein the first pouch cell and the second pouch cell are aligned such that the first bottom surface is in contact with the second top surface, an ejecta barrier located between the first pouch cell and the second pouch cell, wherein the ejecta barrier is configured to be substantially impermeable to a cell ejecta from the first pouch cell, and a vent configured to vent the cell ejecta, wherein the stack battery pack is configured to power a propulsor component.

Abstract: In an aspect, a battery assembly of an aircraft. A battery assembly is configured to include a first plurality of battery cells, a second plurality of battery cells, and an electrical bridging device. A top of each battery cell of first plurality of battery cells is coupled to a first side of an electrical bridging device. A top of each battery cell of a second plurality of battery cells is coupled to a second side of an electrical bridging device.

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.