| 摘要 |
<p>The invention relates to a load introducing element (2), which is intended for a control surface of an aircraft or a spacecraft, and which comprises at least one first component (4) and one second component (8) and one first flange (6), wherein at least one surface area (26) of the first component (4) is adapted to the inner contour of the control surface, wherein the second component (8) exhibits at least one eye (10, 12) for receiving bearing means for mounting the control surface, and wherein a cross sectional profile of the first component (4) exhibits two or more essentially straight legs, which are connected together on their upper side by means of an upper edge, which is adapted to an upper contour of the control surface. Such a load introducing element is produced from a fiber reinforced composite material in an integral type of construction, wherein all of the components are jointly infiltrated and cured. The result of this procedure is a cost effective, stable and lightweight module. Furthermore, the invention relates to a method for producing such a load introducing element (2), to a drive armature (18), to an application and to an aircraft.</p> |
