A blind rivet-nut having an annular-flange-like setting head and a hollow shaft for securing a blind rivet-nut in an opening of a carrier. The hollow shaft has a free end having a threaded portion for receiving a threaded element of a tensioning tool. A clamping portion adjacent to the setting head forms a bead-like deformation when the tensioning tool is used to clamp the carrier between the bead-like deformation and the setting head. A threadless shaft portion is formed between the clamping portion and the threaded portion. The threadless shaft portion is threaded by a thread self-rolling or thread self-tapping fastener. The fastener is received in a positive-locking manner when the fastener is screwed into the thread formed on the previously threadless shaft portion. A method is also disclosed for securing a component to a carrier by a blind rivet-nut.

The disclosure relates to a processing installation for aircraft structural components having a processing station comprising a clamping frame for receiving the structural component, wherein the clamping frame extends along a station longitudinal axis which extends in a longitudinal direction and a processing unit which has an upper tool unit having an upper tool and a lower tool unit, wherein the processing installation has a processing region which is formed by a laterally delimited, first spatial portion in which the clamping frame and the processing unit are arranged during processing, wherein the processing installation has a service region for carrying out service operations, wherein the first spatial portion is separated from the second spatial portion in a transverse direction, wherein a service platform is arranged in the service region and can be positioned in a service plane which is orthogonal to the vertical direction.

The disclosure relates to a processing installation for aircraft structural components having a processing station comprising a clamping frame for receiving the structural component, wherein the clamping frame extends along a station longitudinal axis which extends in a longitudinal direction and a processing unit which has an upper tool unit having an upper tool and a lower tool unit, wherein the processing installation has a processing region which is formed by a laterally delimited, first spatial portion in which the clamping frame and the processing unit are arranged during processing, wherein the processing installation has a service region for carrying out service operations, wherein the first spatial portion is separated from the second spatial portion in a transverse direction, wherein a service platform is arranged in the service region and can be positioned in a service plane which is orthogonal to the vertical direction.

A method and system of attaching rivets to secure sheets of paper together. The rivets have a head, a recess, a skirt and a tail. A tool is configured so that the tail fits through a hole in the tool. Before the tail is inserted into the hole in the tool, the tail is inserted through two holes in the paper(s) and then in the hole in the tool. Pressure is placed on the paper by pressing downward on the tool thereby causing the paper(s) to snap into the recess, thereby securing both pieces of paper together.

A method and system of attaching rivets to secure sheets of paper together. The rivets have a head, a recess, a skirt and a tail. A tool is configured so that the tail fits through a hole in the tool. Before the tail is inserted into the hole in the tool, the tail is inserted through two holes in the paper(s) and then in the hole in the tool. Pressure is placed on the paper by pressing downward on the tool thereby causing the paper(s) to snap into the recess, thereby securing both pieces of paper together.

An apparatus for automated application of rivets to a part is described, in which an operator is not required to manually align a rivet gun with each hole to be riveted or to manually squeeze the rivet into place. The apparatus includes a frame assembly, a tool positioning assembly attached to the frame assembly, and a movable tool assembly engaged with the tool positioning assembly and configured to be moved with respect to the tool positioning assembly. The tool positioning assembly is adjustable to correspond with a position of a number of rivet holes on a part to be riveted. In this way, the movable tool assembly is able to sequentially align with each of a number of rivet holes via alignment with the tool positioning assembly and to apply a rivet to each of the rivet holes.

A cap for a temporary fastener comprises a hollow, cup-shaped body and an inwardly tapered neck. The hollow body fits over a workpiece-engaging portion of the temporary fastener, and the neck extends from the hollow body. The tapered neck terminates in a hollow tip that is sized and configured to fit over aligned holes in the joined workpieces and to contact a minimal surface area of the outermost workpiece to reduce surface damage to the workpieces such that any damage will be removed when the holes are countersunk in the normal course of assembly.

A cap for a temporary fastener comprises a hollow, cup-shaped body and an inwardly tapered neck. The hollow body fits over a workpiece-engaging portion of the temporary fastener, and the neck extends from the hollow body. The tapered neck terminates in a hollow tip that is sized and configured to fit over aligned holes in the joined workpieces and to contact a minimal surface area of the outermost workpiece to reduce surface damage to the workpieces such that any damage will be removed when the holes are countersunk in the normal course of assembly.

The invention relates to a processing installation for aircraft structural components (2) having at least one processing station (3, 4), wherein the processing station (3, 4) has a clamping frame (7, 8) which extends along a longitudinal station axis (5, 6) for receiving the aircraft structural component (2) which is intended to be processed in each case and a processing unit (9, 10), preferably a riveting unit, for processing the aircraft structural component (2) and wherein the clamping frame (7, 8) is articulated so as to be adjustable in terms of height and pivotable to two positioning towers (11, 12) which are arranged in a vertical tower plane (13). It is proposed that there be provided transversely relative to the tower plane (13) a transverse offset of the clamping frame (7, 8) which enables an aircraft structural component (2) to be loaded onto and/or unloaded from the clamping frame (7, 8) along the tower plane (13) and at least one positioning tower (11, 12) to be passed laterally.

The invention relates to a processing installation for aircraft structural components (2) having at least one processing station (3, 4), wherein the processing station (3, 4) has a clamping frame (7, 8) which extends along a longitudinal station axis (5, 6) for receiving the aircraft structural component (2) which is intended to be processed in each case and a processing unit (9, 10), preferably a riveting unit, for processing the aircraft structural component (2) and wherein the clamping frame (7, 8) is articulated so as to be adjustable in terms of height and pivotable to two positioning towers (11, 12) which are arranged in a vertical tower plane (13). It is proposed that there be provided transversely relative to the tower plane (13) a transverse offset of the clamping frame (7, 8) which enables an aircraft structural component (2) to be loaded onto and/or unloaded from the clamping frame (7, 8) along the tower plane (13) and at least one positioning tower (11, 12) to be passed laterally.