Abstract: Hybrid aircraft propulsion systems are disclosed comprising an electrically driven ducted fan, a peripheral duct or enclosure, a combustion-produced source of radiant energy, radiant energy receivers or cold mirrors, and thermophotovoltaic or thermoelectric cell energy converters. An electric motor drives a partially or completely duct enclosed fan. Downstream and within the duct enclosure, radiant energy emitters irradiated receiver fins and thermophotovoltaic cells or thermoelectric cells. The receiver fins heat and expand the fan air, and the thermophotovoltaic cells or thermoelectric cells convert the radiant energy into electrical energy which is available to charge batteries and energize the fan motor. Thrust is provided via the acceleration of air by the fan and by the acceleration of air due to heat driven expansion.