Abstract: A tooling device for producing a planar structural component for an aircraft has a moulding tool part with a contour surface for receiving a planar semi-finished product, a heating device for heating the semi-finished product, a film produced from an elastically deformable material and a clamping system with a first clamping device arranged on a first longitudinal side of the contour surface , and a second clamping device arranged on a second longitudinal side of the contour surface located opposite the first longitudinal side. The film is couplable to the clamping devices by the edge regions thereof and, when it is coupled to the clamping devices, covers the contour surface of the moulding tool part. The film is elastically deformable relative to the contour surface by the first and/or the second clamping device to press the semi-finished product in a planar manner against the contour surface for deforming purposes.

Abstract: A tooling device for producing a planar structural component for an aircraft has a moulding tool part with a contour surface for receiving a planar semi-finished product, a heating device for heating the semi-finished product, a film produced from an elastically deformable material and a clamping system with a first clamping device arranged on a first longitudinal side of the contour surface , and a second clamping device arranged on a second longitudinal side of the contour surface located opposite the first longitudinal side. The film is couplable to the clamping devices by the edge regions thereof and, when it is coupled to the clamping devices, covers the contour surface of the moulding tool part. The film is elastically deformable relative to the contour surface by the first and/or the second clamping device to press the semi-finished product in a planar manner against the contour surface for deforming purposes.

Abstract: A tooling device for producing a planar structural component for an aircraft has a moulding tool part with a contour surface for receiving a planar semi-finished product, a heating device for heating the semi-finished product, a film produced from an elastically deformable material and a clamping system with a first clamping device arranged on a first longitudinal side of the contour surface, and a second clamping device arranged on a second longitudinal side of the contour surface located opposite the first longitudinal side. The film is couplable to the clamping devices by the edge regions thereof and, when it is coupled to the clamping devices, covers the contour surface of the moulding tool part. The film is elastically deformable relative to the contour surface by the first and/or the second clamping device to press the semi-finished product in a planar manner against the contour surface for deforming purposes.

Abstract: A fuselage includes a fuselage section with an inner surface having a non-circular contour and a spherical pressure bulkhead with an outer edge. The outer edge of the spherical pressure bulkhead is attached to the inner surface of the fuselage section and extends along a line, which is non-circular. The line extends in a three-dimensional space extending parallel to the inner surface of the fuselage section. An aircraft and a method for manufacturing a fuselage are also described.

Abstract: A fuselage section of an aircraft has an inner surface with a non-circular contour. A pressure bulkhead for use in the fuselage section has a non-circular outer edge that is aligned with the non-circular contour of the inner surface of the fuselage section. The pressure bulkhead has a spherically-shaped inner section having radially arranged stiffening units and a non-spherically outer section having additional radially arranged stiffening units; the stiffening units corresponding to each section do no extend into the other section. The pressure bulkhead is attached to the fuselage section. A method of manufacturing a fuselage section having such a pressure bulkhead is also provided.

Abstract: A tooling device for producing a planar structural component for an aircraft has a moulding tool part with a contour surface for receiving a planar semi-finished product, a heating device for heating the semi-finished product, a film produced from an elastically deformable material and a clamping system with a first clamping device arranged on a first longitudinal side of the contour surface, and a second clamping device arranged on a second longitudinal side of the contour surface located opposite the first longitudinal side. The film is couplable to the clamping devices by the edge regions thereof and, when it is coupled to the clamping devices, covers the contour surface of the moulding tool part. The film is elastically deformable relative to the contour surface by the first and/or the second clamping device to press the semi-finished product in a planar manner against the contour surface for deforming purposes.

Abstract: A fuselage skin window unit for an aircraft, an aircraft with such a fuselage skin window unit and a method for manufacturing such a fuselage skin window unit are described. The fuselage skin window unit includes a fuselage skin section and a window pane section. The fuselage skin section is part of a fuselage skin of the aircraft and has a pattern of pinhole perforations. The window pane section is transparent and arranged so that it covers the pinhole perforations.

Abstract: This pertains to an aircraft structure with a first shell-shaped structural element and a second shell-shaped structural element. The aircraft structure comprises a strap, wherein the first shell-shaped structural element and the second shell-shaped structural element are respectively fastened on the strap by means of a rivet joint. An edge of the first shell-shaped structural element extends on a surface of the strap along a predefined curve with periodic progression. An edge of the second shell-shaped structural element likewise extends on the surface of the strap parallel to the curve with periodic progression. The invention furthermore pertains to an aircraft with an aircraft structure, as well as a method for manufacturing an aircraft structure.

Abstract: This relates to a fuselage section comprising an inner surface with a non-circular contour and a pressure bulkhead comprising a non-circular outer edge. The non-circular outer edge of the pressure bulkhead is aligned with the non-circular contour of the inner surface of the fuselage section when the pressure bulkhead is attached to the fuselage section. This further relates to an aircraft with a fuselage section and a method for manufacturing a fuselage section.

Abstract: A fuselage includes a fuselage section with an inner surface having a non-circular contour and a spherical pressure bulkhead with an outer edge. The outer edge of the spherical pressure bulkhead is attached to the inner surface of the fuselage section and extends along a line, which is non-circular. The line is a three-dimensional curve extending parallel to the inner surface of the fuselage section. An aircraft and a method for manufacturing a fuselage are also described.