Patent attributes
An integral hybrid electric aircraft system including a fuselage including an electrical energy source, wherein the electrical energy source includes a plurality of batteries and a fuel tank, and wherein the fuel tank contains fuel. The fuselage also including a generator in fluid communication with the fuel tank. The generator generates electricity using the fuel from the fuel tank. The system including a set of propulsors, wherein each propulsor of the set of propulsors is electrically connected to the electrical energy source and the generator and wherein the set of propulsors is configured to be powered by the generator during fixed-wing flight. The set of propulsors including at least a pusher propulsor configured to provide forward thrust and at least a lift propulsor configured to provide lift.
