Patent ID: 7698990
Filing Date: 2010-04-20
Classification: F15B

Abstract:
1. A hydraulic linear actuating drive for an aircraft arrangement comprising: a cylinder with a first end and a second end, the first and the second ends opposing one another; a movable servo piston capable of being pressure-loaded and running inside the cylinder, wherein the movable servo piston separates two operating chambers; a hydraulic working fluid occupying both of the two operating chambers; a first and a second piston rod attached to the servo piston, wherein the first piston rod protrudes from the first end, and wherein the second piston rod protrudes from the second end, and wherein the first piston rod is attached to an actuating element; at least one piston gasket having at least two sealing elements disposed at a distance from each other, an intermediate space being defined between the at least two sealing elements, an inner wall of the cylinder and an outer edge of the servo piston; at least one leakage channel moveable together with the servo piston and having a first end opening into a leakage fluid inlet opening located in the intermediate sealing space and a second end opening into a leakage fluid outlet opening arranged outside of the cylinder; and a valve disposed outside of the cylinder on the leakage fluid outlet opening, the valve opening towards an outside of the leakage channel and closing towards an inside of the leakage channel.