US Patent 11174035 Hybrid flight vehicle

In a hybrid flight vehicle, having four rotors configured to produce thrust to propel a frame, a gas turbine engine incorporating a compressor and a first turbine adapted to rotate integrally with the compressor, a generator configured to generate electric power, a battery configured to store power generated by the generator, four motor-generators connected to the battery and the multiple rotors to drive the rotors when power is supplied from the battery, while generating power when driven by the rotors. In the vehicle, there is provided a second turbine provided independently of the gas turbine engine and configured to drive the rotors when supplied high pressure gas outputted from the gas turbine engine.