Patent ID: 7506842

Claim:
An actuator control system for an aircraft, comprising: first and second aircraft control portions; a source of fluid on the aircraft; first and second supply lines and a return line coupleable to the source of fluid; a fluid-driven actuator connected to at least one of the first and second control portions, the fluid-driven actuator in fluid communication with the first and second supply lines; a flow control assembly connected to the first supply line and to the return line and configured to control the flow of fluid in one direction from the first supply line to the fluid-driven actuators and to control the flow of fluid in another direction from the fluid-driven actuator to the return line; a bypass line connected to the first and second supply lines and positioned to provide fluid from the second supply line into the first supply line at a position intermediate the source and the flow control assembly, the bypass line being configured to allow local recycling of the fluid from the second supply line to the first supply line at the position intermediate the source and the flow control assembly to drive the actuator; a primary power system operatively coupled to the fluid-driven actuator; and a dedicated alternate power system coupled to the fluid-driven actuator with the alternate power system being provided for dedicated operation of the fluid-driven actuator.