Aircraft structural component

An aircraft structural component, comprising:

• a skin element, which includes an inner surface and an outer surface;
• a multitude of transverse stiffening elements, which lie spaced apart from each other against the inner surface of the skin element;
• and
• a multitude of longitudinal stiffening elements, which lie spaced apart from each other and transverse to the transverse stiffening elements against the inner surface of the skin element;
• wherein the skin element includes a multitude of skin sections, each of which is defined between two neighboring transverse stiffening elements and two neighboring longitudinal stiffening elements,
• wherein between a first and a second transverse stiffening element and between a first and a second longitudinal stiffening element, a first skin section is defined,
• wherein, in the first skin section on the inner surface of the skin element a first applied reinforcement is mounted,
• wherein the first applied reinforcement includes a core layer lying against the inner surface of the skin element and having a circumferential contour line on the inner surface of the skin element,
• wherein the first applied reinforcement includes a face sheet surrounding the core layer on a side of the core layer which faces away from the skin element, which face sheet is directly attached to the skin element along the circumferential contour line of the core layer, such that the core layer is entirely enclosed between the face sheet and the inner surface of the skin element,
• wherein the face sheet is formed integrally with either one of or both of the first longitudinal stiffening element and the second longitudinal stiffening element, and
• wherein the circumferential contour line of the core layer has a shape which is lenticular, elliptical or circular when viewed perpendicular to the inner surface.