Patent attributes
A hybrid propulsion system for an electric aircraft, the system including an electric aircraft including a fuselage. The fuselage including an energy source containing electric power. The electric aircraft further including at least a laterally extending element attached to the fuselage and extending laterally from the fuselage. The electric aircraft further including at least a propulsor electrically connected to the energy source. The system also including at least a power unit pod attached to the at least a laterally extending element and including an auxiliary power unit configured to generate electric power. The power unit pod also including a fuel tank in fluid communication with the auxiliary power unit and a power output line electrically connected to the energy source of the electric aircraft.
