A hybrid-electric propulsion (HEP) system is provided that includes a gas turbine engine, an electrical power motive system, a system controller, and a propulsor. The gas turbine engine has a free turbine configuration and a compressor. The electrical power motive system has first and second electric motors and first and second inverters. The gas turbine engine provides motive force to the propulsor. The first electric motor is configurable in a drive mode or in generator mode. The second electric motor is in communication with the compressor. The system controller is in communication with the gas turbine engine, the first and second inverters, and a non-transitory memory storing instructions, which instructions cause the system controller to control the second inverter to operate the second electric motor to provide a motive force to the compressor of the gas turbine engine during a low power setting of the gas turbine engine.

An airship comprises a plurality of electric power generators; a plurality of electrical buses; and a plurality of propulsion points each equipped with a propellant bundle formed from a plurality of thrusters of the electric-motor-driven propeller type. For each of the propulsion points, a thruster is electrically connected to one of the generators by way of one of the electrical buses, and another thruster of the propulsion point is electrically connected to another of the generators by way of another of the electrical buses.

A system of a hybrid aircraft includes a first gas turbine engine, a second gas turbine engine, a power source, and a controller. The first gas turbine engine includes a first electric machine. The second gas turbine engine includes a second electric machine. The controller is operable to determine an operating condition of the first gas turbine engine and the second gas turbine engine and to detect a change in a thrust command for the hybrid aircraft. The controller is further operable to determine an adjustment to the second electric machine to compensate for the change in the thrust command while the first gas turbine engine is operating in a fuel-driven mode and the second gas turbine engine is operating in an electrically-driven mode. At least a portion of electric power to perform the adjustment to the second electric machine is extracted from the power source.

Provided is a secondary battery where a positive electrode includes a first covered part covered with a positive electrode active material layer and a positive electrode active material non-covered part on a positive electrode foil, and a negative electrode includes a second covered part covered with a negative electrode active material layer and a negative electrode active material non-covered part on a negative electrode foil, one or both of the positive electrode active material non-covered part and the negative electrode active material non-covered part have a surface formed by bending toward the central axis of the wound structure and overlapping each other, and the surface is joined to the positive electrode current-collecting plate or the negative electrode current-collecting plate.

A hybrid propulsion unit for an aircraft with multi-rotor rotary wings includes an electrical generator driven by an internal combustion engine, a rectifier configured to convert an AC current sent by the electrical generator into DC current, a DC-AC converter, an electrical network connecting the rectifier to the converter and including a high-voltage DC current bus, electric motors powered by propeller converters coupled to the electric motors, electrical energy storage connected to the electrical network, the electrical storage including at least one primary storage element and at least one secondary storage element.

Provided is a secondary battery including: an electrode wound body that has a positive electrode and a negative electrode stacked with a separator interposed therebetween and has a wound structure; and a positive electrode current collecting plate and a negative electrode current collecting plate, accommodated in an exterior can, where the positive electrode includes a first covered part covered with a positive electrode active material layer and a positive electrode active material non-covered part on a positive electrode foil, and the negative electrode includes a second covered part covered with a negative electrode active material layer and a negative electrode active material non-covered part on a negative electrode foil.

A secondary battery including an electrode wound body having a structure in which a positive electrode and a negative electrode are stacked and wound with a separator interposed therebetween, a positive electrode current collector plate; a negative electrode current collector plate, and an exterior can that accommodates the electrode wound body, the positive electrode current collector plate, and the negative electrode current collector plate. The positive electrode has a first covered portion covered with a positive electrode active material layer and a positive electrode active material non-covered portion on a band-shaped positive electrode foil, and the negative electrode has a second covered portion covered with a negative electrode active material layer and a negative electrode active material non-covered portion on a band-shaped negative electrode foil.

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.

One method for ejecting a battery from an electric flying vehicle includes monitoring one or more batteries providing power to the electric flying vehicle during a flight, determining when at least one of those batteries is operating as a hazardous battery posing a safety risk to the electric flying vehicle while in flight, activating an ejection system disconnecting the hazardous battery from a chassis of the electric flying vehicle, and ejecting the hazardous battery from the electric flying vehicle during the flight. The system operating this process may include a sensor that monitors the operating state of the batteries, a controller in communication with the sensor for determining when the one or more of the batteries is hazardous, and an actuator opening enough of the housing to permit ejection of the hazardous battery out from within the electric flying vehicle midflight.

A method of determining a remaining operating time of an electrical energy storage unit in an aircraft, comprising: using a first sensor arrangement for measuring first performance parameters of the electrical energy storage unit; determining first performance indicators based on the first performance parameters; using at least one second sensor arrangement for measuring second performance parameters of the electrical energy storage unit; determining second performance indicators based on the second performance parameters; comparing the first performance indicators with the second performance indicators to determine consolidated performance indicators; and determining predictive remaining operating times of the electrical energy storage unit based on the consolidated performance indicators, wherein the predictive remaining operating times comprise at least a predictive nominal remaining operating time and a predictive emergency remaining operating time.