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 system for monitoring moisture content in a battery pack of an electric aircraft. The system includes a at least an energy storage element, a user interface configured to display moisture content datum to a user, and at least a sensor. At least a sensor is configured detect a moisture content datum of the energy storage element and communicate with the energy storage element. The system also includes a computing device communicatively connected to the at least a sensor. That computing device is configured to generate a notification as a function of the moisture content datum and transmit the notification to a user interface.

Abstract: In an aspect of the present disclosure is a system for cooling a high voltage (HV) cable on an electric aircraft, including a fuselage configured to receive the HV cable, including a first side comprising a first venting closure movable between an open position and a closed position. The fuselage may further comprise a second side opposite the first side, the second side comprising a second venting closure movable between an open position and a closed position; wherein the first and second venting closures are configured to create a cooling channel between the first and second venting closures when the first and second venting closures are in the open position, wherein the cooling channel contacts the HV cable.

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: An aircraft with increased crash robustness including a fuselage with a forward end, an opposite rear end, a ventral surface, and a dorsal surface. The aircraft further including a longitudinal axis running from the rear end to the forward end and a dorsoventral axis orthogonal to the longitudinal axis and running from the dorsal surface to the ventral surface. The aircraft also including at least a battery module located within the fuselage comprising a plurality of battery cells, each battery cell includes an axial axis positioned orthogonally to each of the longitudinal axis and the dorsoventral axis, and each battery cell has a plurality of radial axes orthogonal to the axial axis, wherein the plurality of radial axes includes a first radial axis aligned with the longitudinal axis and a second radial axis aligned with the dorsoventral axis.

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: 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.

Abstract: In an aspect of the present disclosure is a system for cooling a high voltage (HV) cable on an electric aircraft, including a fuselage configured to receive the HV cable, including a first side comprising a first venting closure movable between an open position and a closed position. The fuselage may further comprise a second side opposite the first side, the second side comprising a second venting closure movable between an open position and a closed position; wherein the first and second venting closures are configured to create a cooling channel between the first and second venting closures when the first and second venting closures are in the open position, wherein the cooling channel contacts the HV cable.

Abstract: The present invention is a system and methods for preconditioning a power source of an electric aircraft. The system may include a sensor attached to a power source of an electric aircraft, where the sensor is configured to detect a condition datum of an operating component of the power source, and a flight controller communicatively connected to the sensor, the flight controller configured to determine if there is a divergent element of an operating state of the power source and, if so, initiate a power source modification to correct the divergent element.

Abstract: Abstract of the Disclosure: 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.

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: A two-dimensional imaging system and a two-dimensional or three-dimensional optical tomographic mapping system, each employing gas scintillation induced by ionizing radiation, i.e., radioluminescence, and corresponding methods, are disclosed. The systems may employ one or more cameras and corresponding UV filters (potentially solar blind filters) for imaging a radioluminescent scene. For two-dimensional or three-dimensional mapping, the resultant UV images are spatially registered with one another and then reconstructed to form a three-dimensional tomographic map of the ionizing radiation. The two-dimensional map is a plane of the three-dimensional map. The UV images may be spatially registered by using a reference source, optionally, a calibrated reference source allowing dosimetry calculations for the ionizing radiation. Molecular nitrogen is the primary candidate for the radioluminescent gas, though a controlled ambient in a chamber of nitric oxide, argon, krypton, or xenon may be employed.

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: 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: A system 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: 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 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: The present invention is a system and methods for preconditioning a power source of an electric aircraft. The system may include a sensor attached to a power source of an electric aircraft, where the sensor is configured to detect a condition datum of an operating component of the power source, and a flight controller communicatively connected to the sensor, the flight controller configured to determine if there is a divergent element of an operating state of the power source and, if so, initiate a power source modification to correct the divergent element.

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: 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.