A system configured to control power transfer of an aircraft engine includes a variable frequency generator (VFG) including a generator configured to direct alternating current to a first rectifier configured to convert alternating current from the VFG to direct current and drive it to a High Voltage DC (HVDC) Bus Network and a second variable frequency generator configured to direct alternating current to a second rectifier configured to convert alternating current from the second generator to direct current and direct it to the HVDC Bus Network, a speed correcting gearbox operatively connected to the VFG configured to align generator frequency to the second generator frequency, a VFG control unit operatively connected to the generator and to the electric module configured to control the VFG, and a second generator control unit operatively connected to the second generator and the HVDC Bus Network configured to control the second generator.

The first VFG can be operatively connected to a low-pressure spool gearbox spool configured to control an engine of an aircraft and the speed-correcting gearbox can be located between the VFG and the low pressure gearbox. The second generator can be operatively connected to a high-pressure gearbox spool configured to control the engine of the aircraft. The output of the first rectifier can be 540 volts and the output of the second rectifier can be 540 volts.

The HVDC Bus Network includes a pair of independent DC busses configured to distribute power.