Hybrid propulsion system for aircraft

Abstract

Hybrid propulsion integral systems for a fixed wing aircraft, and a V/STOL aircraft. A core of the jet engine rotates an integral generator, that provides current to charge batteries located in various locations on an aircraft. The batteries and generator are selectively used to power electric motor(s) that provide the sole source of torque (power) to fans, propellers, or rotors that propel the aircraft, along with a fuel operated gas turbine. In addition, for a V/STOL air vehicle, a hybrid propulsion system fixed to a wing or split between wing and empennage, with moving integral submodules, such as a multifunctional thrust vectoring exhaust nozzle and electrically operated tiltable propeller(s). These differ from the prior configurations by provisioning integrated architectures as delineated.