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: 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: Aspects relate to systems and methods for manufacture of a battery pack including a metal case circumscribing an inner volume circumscribed on all but one open side, where the case additionally includes a sealing rim positioned at least partially about the open side, a first component that includes at least two or more sides of the case, and a second component that includes at least one other side of the case, at least a battery module installed within the inner volume of the case, and an inner panel installed within the inner volume, between the case and the at least a battery module. In some aspects, sealing rim, first component, and second component are all joined together by welding.

Abstract: An electric aircraft with a battery pack for failure safety is provided. The battery pack may be disposed within a fuselage of the electric aircraft. The battery pack may include a crush zone having energy absorbing material configured to compress as a function of a crash force.

Abstract: Aspects relate to systems and methods of use for a crash safe battery pack that includes a case, a first battery module located within the case and mounted to the case with at least a breakaway mount, a second battery module located within the case, a frangible connection configured to provide electrical conduction between the first battery module and the second battery module, and a die configured to contact and separate the frangible connection when the crash safe battery pack is impacted with a sufficiently great connection breaking force.

Abstract: Aspects relate to systems and methods for manufacture of a battery pack including a metal case circumscribing an inner volume circumscribed on all but one open side, where the case additionally includes a sealing rim positioned at least partially about the open side, a first component that includes at least two or more sides of the case, and a second component that includes at least one other side of the case, at least a battery module installed within the inner volume of the case, and an inner panel installed within the inner volume, between the case and the at least a battery module. In some aspects, sealing rim, first component, and second component are all joined together by welding.

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: A battery pack for failure safety includes a pack casing, a battery module of a plurality of battery modules secured to the pack casing by a battery module connection, a crush zone located beneath the battery module, wherein the crush zone comprises an energy absorbing material configured to compress as a function of the battery module and a crash force, and wherein the battery module connection releases the battery module into the crush zone guided by the inner lining.

Abstract: Aspects relate to systems and methods of use for a crash safe battery pack that includes a case, a first battery module located within the case and mounted to the case with at least a breakaway mount, a second battery module located within the case, a frangible connection configured to provide electrical conduction between the first battery module and the second battery module, and a die configured to contact and separate the frangible connection when the crash safe battery pack is impacted with a sufficiently great connection breaking force.