Support and actuation device for an aircraft control element, in particular for a rudder, wingtip or aircraft door.

Abstract

The invention relates to a support and actuation device for a control element of an aircraft, in particular for a rudder, a pivoting wingtip or a door of an aircraft, which includes a hydraulic cylinder system for performing linear motion, a crank mechanism for transforming the linear motion into a rotational motion, to move the control element accordingly, and is characterized in that the hydraulic cylinder system includes a double-acting hydraulic cylinder, preferably a double-acting hydraulic cylinder.