Patent ID: 8430354

Claim:
An aircraft flight control system comprising: power takeoff means connected to engines of the aircraft; actuators for driving mobile devices of the aircraft; circuits connecting said power takeoff means to said actuators and transmitting energy for supplying said actuators with powering energy from said power takeoff means in which all the power takeoff means are electricity generators and all the circuits comprise an electricity transmission segment adjacent to the power takeoff means, wherein the power takeoff means belong to two different categories and comprise at least one electrical generator outputting electricity having a variable frequency and variable amplitude voltage changing with a constant voltage-to-frequency ratio, the actuators of the circuits connected to said at least one electrical generator comprise electro-hydraulic pumps, which are supplied with said electricity having a variable frequency and variable amplitude voltage changing with a constant voltage-to-frequency ratio, said electrical generator outputting a variable frequency and variable amplitude voltage changing with a constant voltage-to-frequency ratio is connected to said electro-hydraulic pumps without power electronics, and the electro-hydraulic pumps comprise input shafts that are controlled at a rotation speed varying proportionally to a speed of said engines of the aircraft.