Abstract: A stiffened structural component for an aircraft includes a first material sheet with a first surface, and at least one elongate bulge that bulges out in a direction transverse to the first surface in order to stiffen the structural component, wherein each of the at least one bulge comprises two edges that extend along the first surface, wherein a continuous bulging surface extends between the edges, and wherein the bulges are formed integrally into the first material sheet through pressing.

Abstract: A stiffened structural component for an aircraft includes a first material sheet with a first surface, and at least one elongate bulge that bulges out in a direction transverse to the first surface in order to stiffen the structural component, wherein each of the at least one bulge comprises two edges that extend along the first surface, wherein a continuous bulging surface extends between the edges, and wherein the bulges are formed integrally into the first material sheet through pressing.

Abstract: The present invention relates to a method of monitoring the condition of structural components, in which an optical sensor in conjunction with a computing unit ascertains image deviations from successive images of the structural components to be monitored, and therefrom ascertains changes in shape of the structure. Robust three-dimensional scanning of the structural components is possible when using two or more sensors. The invention further relates to an apparatus for monitoring the condition of structural components having an optical sensor and an apparatus having two or more sensors. Finally the invention relates to an aircraft in which the methods or apparatuses according to the invention are used.

Abstract: The present invention relates to a method of monitoring the condition of structural components, in which an optical sensor in conjunction with a computing unit ascertains image deviations from successive images of the structural components to be monitored, and therefrom ascertains changes in shape of the structure. Robust three-dimensional scanning of the structural components is possible when using two or more sensors. The invention further relates to an apparatus for monitoring the condition of structural components having an optical sensor and an apparatus having two or more sensors. Finally the invention relates to an aircraft in which the methods or apparatuses according to the invention are used.

Abstract: A structural component for example an aircraft door or aircraft body section is cast of lightweight metals as an integral structure with an outer skin reinforced by stiffening ribs forming a first grid structure and by stiffening walls forming a second gird structure integrally connected to the first grid structure as a result of casting. The side opposite the skin on the second grid structure is preferably covered by a further inner skin, for example secured by casting or by an adhesive.

Abstract: A structural component for example an aircraft door or aircraft body section is cast of lightweight metals as an integral structure with an outer skin reinforced by stiffening ribs forming a first grid structure and by stiffening walls forming a second gird structure integrally connected to the first grid structure as a result of casting. The side opposite the skin on the second grid structure is preferably covered by a further inner skin, for example secured by casting or by an adhesive.