Patent ID: 8039983

Claim:
An aircraft system, comprising: a turbofan engine that includes: a compressor; a first turbine; a high pressure shaft connected between the compressor and the first turbine; a fan; a second turbine; and a low pressure shaft connected between the fan and the second turbine, the low pressure shaft being disposed annularly around the high pressure shaft; a synchronous starter/generator; a first constant speed drive connected between the high pressure shaft and the starter/generator, the first constant speed drive being positioned to receive a first mechanical input rotating at a first variable rate, and provide a first mechanical output rotating at a first generally constant rate; a synchronous generator; a second constant speed drive connected between the low pressure shaft and the generator, the second constant speed drive being positioned to receive a second mechanical input rotating at a second variable rate, and provide a second mechanical output rotating at a second generally constant rate that is generally the same as the first constant rate; a common bus electrically connected between the starter/generator and the generator, the bus being positioned to receive electrical power from the starter/generator that is in phase with and at the same frequency as power received from the generator; and a controller operatively coupled to the starter/generator and the generator.