What is claimed is:1. A system comprising:a variable frequency generator (VFG) including a generator configured to conduct alternating current to a first rectifier configured to convert alternating current from the VFG to direct current and drive it to an HVDC Bus Network;a second variable frequency generator including a second generator configured to conduct 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 a generator frequency to a second generator frequency;a VFG control unit operatively connected to the generator configured to control the VFG input speed and regulation; anda second generator control unit operatively connected to the second generator and the HVDC Bus Network configured to control the second generator regulation;wherein the VFG is operatively connected to a low-pressure spool gearbox spool engine of an aircraft and the speed-correcting gearbox is located between the VFG and the low-pressure spool gearbox.2. The system of claim 1, wherein the second generator is operatively connected to a high-pressure gearbox spool engine of the aircraft.3. The system of claim 1, wherein the output of the first rectifier is 540 volts.4. The system of claim 1, wherein the output of the second rectifier is 540 volts.5. The system of claim 1, wherein the HVDC Bus Network includes a pair of independent DC busses configured to distribute power.6. The system of claim 1, wherein the system is configured to control power transfer of an aircraft engine.7. A method comprising:placing a speed-correcting gearbox between a first generator and a low-pressure gearbox;driving alternating current from the first generator connected to the low pressure gearbox spool;driving alternating current from a second generator connected to a high pressure gearbox spool; andaligning a frequency output of the first generator to a frequency output of the second generator in order to control performance parameters of a direct current system of an aircraft.8. The method of claim 7, further comprising reducing voltage ripple.9. The method of claim 7, further comprising reducing load ripple.10. The method of claim 7, wherein the first generator (VFG) conducts 115/230 volts AC to a first rectifier which converts to 540 Vdc output.11. The method of claim 7, wherein the second generator conducts 115/230 volts AC to a second rectifier which converts to 540 Vdc output.