Abstract: A device for producing textile planar structures formed of a plurality of portions deposited beside one another of fiber rovings. A supply device provides a fiber rovings at a transfer installation. A plurality of path guiding rails are disposed beside one another and above the depositing face. A gripper unit and a cutting unit are disposed on each path guiding rail. Each gripper unit and each cutting unit is movable and positionable along the path guiding rail independently of the gripper units and cutting units of the other path guiding rails. The gripper units grab the fiber roving from the transfer installation and move their free end to a desired terminal position. The cutting units severs the rovings at a cutting position. The gripper units and the cutting units have a downholder for pressing the fiber roving against the depositing face.

Abstract: A method for producing a load introducing element for a control surface of an aircraft or a spacecraft, includes cutting to size preformed fibrous substructures out of a fibrous material. The method also includes draping the fibrous substructures to mold at least one first component, at least one second component and at least one first flange in the form of a single semi-finished product. Further, the method includes inserting the semi-finished product into a mold, injecting matrix material, and curing said semi-finished product to form a finished product.

Abstract: A load introducing element for a control surface of an aircraft or a spacecraft comprises at least one first component, one second component and one first flange. At least one surface area of the first component is adapted to conform to the inner contour of the control surface. The second component has at least one eye for receiving bearing means for mounting the control surface. A cross sectional profile of the first component has two or more essentially straight legs, which are connected together on their upper side by an upper edge which is adapted to an upper contour of the control surface. The load introducing element is formed by a fiber reinforced composite material having an integral type of construction in which all of the components are jointly infiltrated and cured. The invention also provides a method for producing such a load introducing element, a drive armature and an aircraft that includes such a load bearing element.