Abstract: An apparatus for preconditioning a power source of an electric aircraft is presented. The apparatus includes a power source of an electric aircraft, a computing device, and a user device. The computing device is configured to receive a flight plan, determine a predicted power usage model as a function of the flight plan, and initiate a power source modification on the electric aircraft as a function of the predicted power usage model. The user device is configured to display a flight performance infographic as a function of the predicted power usage model.

Abstract: A cooling assembly for preventing cell-to-cell heat transfer is provided. Cooling assembly may include a battery pack, which may include a plurality of battery cells. Cooling assembly may also include a cooling plate. Cooling plate may include a geometry that prevents battery cells from exchanging heat during operation and/or malfunctions. Cooling plate geometry may include geometric features imprinted in a surface of cooling plate.

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 redistributing electrical load in an electric aircraft. The system includes a ring bus and a controller communicatively connected to the ring bus. The ring bus includes a plurality of bus sections including a first bus section and a second bus section. The controller is configured to receive a fault datum indicative of a fault associated with one of a first energy source and a second energy source, actuate, as a function of the fault datum, at least a switch to electrically connect the first bus section and the second bus section so as to form an electrical merger of the first bus section and the second bus section, and redistribute the electrical load to compensate for the fault associated with one of the first energy source and the second energy source. A method of redistributing electrical load in an electric aircraft is also provided.

Abstract: A system for battery pack cooling including a battery pack. The battery pack includes a plurality of pouch cells and a separation element, where the separation separates at least a first pouch cell of the plurality pouch cells from a second pouch cell of the plurality of pouch cells. The separation element contains a fluid. The system also includes a cooling plate, where the cooling plate is adjacent to the lower side of the battery pack. The cooling plate comprises at least a cooling fin, where the at least a cooling fin extends towards the separation element.

Abstract: A system for battery pack cooling including a battery pack. The battery pack includes a plurality of pouch cells and a separation element, where the separation separates at least a first pouch cell of the plurality pouch cells from a second pouch cell of the plurality of pouch cells. The separation element contains a fluid. The system also includes a cooling plate, where the cooling plate is adjacent to the lower side of the battery pack. The cooling plate comprises at least a cooling fin, where the at least a cooling fin extends towards the separation element.

Abstract: A system for redistributing electrical load in an electric aircraft. The system includes a ring bus and a controller communicatively connected to the ring bus. The ring bus includes a plurality of bus sections including a first bus section and a second bus section. The controller is configured to receive a fault datum indicative of a fault associated with one of a first energy source and a second energy source, actuate, as a function of the fault datum, at least a switch to electrically connect the first bus section and the second bus section so as to form an electrical merger of the first bus section and the second bus section, and redistribute the electrical load to compensate for the fault associated with one of the first energy source and the second energy source. A method of redistributing electrical load in an electric aircraft is also provided.

Abstract: A venting assembly for battery ejecta on a side different from an egress, wherein the venting assembly comprises a plurality of battery packs configured to power the electric aircraft, wherein each battery pack of plurality of battery packs comprises a plurality of battery cells, 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 a different side of the electric aircraft as an egress.

Abstract: The present invention is directed to an apparatus for managing thermal energy of an electric aircraft energy source. Apparatus may include fins, which extend from a skin of electric aircraft. The energy source may bias or be adjacent to the fins so that heat energy may dissipate from the energy source and through the fins and, thus, the skin. A coolant may also be run through the apparatus, where the coolant may flow through channels that are disposed between the fins.

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: 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: A device for emergency disconnection of a high voltage electrical connection between a power source and a high voltage component of an electric aircraft in response to a crash. The device includes a controller, where the controller is configured to receive a sensor datum from a sensor of device, to determine a crash element between and initiate a disconnection protocol as a function of the crash element.

Abstract: The present invention is directed to an apparatus for managing thermal energy of an electric aircraft energy source. Apparatus may include fins, which extend from a skin of electric aircraft. The energy source may bias or be adjacent to the fins so that heat energy may dissipate from the energy source and through the fins and, thus, the skin. A coolant may also be run through the apparatus, where the coolant may flow through channels that are disposed between the fins.

Abstract: A method and system for ground-based thermal conditioning of an electric aircraft. The system includes an electric aircraft, an onboard thermal conditioning module on the electric aircraft, and a ground-based thermal conditioning module connected to the onboard thermal conditioning module. Liquid coolant runs through the ground-based thermal conditioning module to the onboard thermal conditioning module. Ground-based thermal conditioning module purges the coolant from the onboard thermal conditioning module. The ground-based thermal conditioning module is disconnected from the onboard thermal conditioning module.

Abstract: A heat transfer system for controlling two or more heat loads, including a high transient heat load, is provided. The heat transfer system may include sensible-heat thermal energy storage. A method of transferring heat from two or more heat loads to an ambient environment is further provided.

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: 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: Methods are provided for controlling thermal energy storage in a thermal energy management system that may operate in response to a variable or high transient heat load. Thermal energy management systems are also provided for controlling thermal energy storage that may operate in response to a variable or high transient heat load.

Abstract: In an aspect an electric aircraft is presented. An electric aircraft includes a consumable coolant reservoir housed within the electric aircraft. A consumable coolant reservoir is configured to contain a coolant. An electric aircraft includes a battery pack temperature control system including at least a thermal pathway. A thermal pathway is in thermal communication with a consumable coolant reservoir and at least a battery pack of an electric aircraft. A thermal pathway is configured to transport a thermal energy away from at least a battery pack.

Abstract: Provided in this disclosure is a high voltage distribution system of an electric aircraft. The system includes a power source mechanically connected to an electric aircraft, where the power source is configured to supply power to the electric aircraft. The system also includes a flight component mechanically connected to the electric aircraft. The system also includes a distribution component configured to control the providing of power to and from the power source and the flight component as needed during recharging and/or operation of the electric aircraft.