Abstract: A production system for automated assembly of vehicle components, in particular for automated assembly of structural components of an aircraft or spacecraft.

Abstract: A separating film with an anti-adhesion layer for preventing an adhesive connection between a thermally curable levelling compound, applied in the region of a joining zone of a first component, and a joining zone of a second component to be joined to the first component. The anti-adhesion layer is provided, at least in parts, with a heating layer. As a result of the actively electrically heatable heating layer of the separating film, which is an integral part of the separating film, the processing time for joining two components, which are subject to tolerances, using a thermally curable levelling compound (known as liquid shimming), can be reduced by at least 40% compared with the conventional process.

Abstract: A production system for automated assembly of vehicle components, in particular for automated assembly of structural components of an aircraft or spacecraft.

Abstract: A clamping system for positioning a first component and a second component relatively to each other includes a clamping device, a separating foil and an electrical contacting device. The clamping device is adapted to fix the first and second components in a desired joining position under creation of a gap therebetween with a characteristic measure of tolerance relative to each other in a first position of the clamping device and to release this fixation in a second position of the clamping device. The separating foil includes an anti-stick layer and a heating layer connected with electrically conducting contact zones for heating a compensation compound arranged in the gap. The electrical contacting device is mechanically couplable with the clamping device or a supporting device holding the clamping device and is adapted for creating an electrical contact with the contact zones at least in the first position of the clamping device.

Abstract: A method for joining a first and a second component, at least one of which comprises a fiber-reinforced plastics material. The components are arranged in relation to one another in such a way that a gap region remains between the first and the second component. The gap region is filled, at least in portions, with an uncured plastics material filler in which nanoparticles are dispersed. Energy is introduced locally into the nanoparticles in order to cure the plastics material filler. In another aspect, the invention provides a device for joining two components.

Abstract: A clamping system for positioning a first component and a second component relatively to each other includes a clamping device, a separating foil and an electrical contacting device. The clamping device is adapted to fix the first and second components in a desired joining position under creation of a gap therebetween with a characteristic measure of tolerance relative to each other in a first position of the clamping device and to release this fixation in a second position of the clamping device. The separating foil includes an anti-stick layer and a heating layer connected with electrically conducting contact zones for heating a compensation compound arranged in the gap. The electrical contacting device is mechanically couplable with the clamping device or a supporting device holding the clamping device and is adapted for creating an electrical contact with the contact zones at least in the first position of the clamping device.

Abstract: A method for joining parts to be joined which are subject to tolerance in the aerospace sector. The method involves determining the geometric data of a first and second part to be joined, determining the joining gap dimensions of the first and second parts from the determined geometric data and arranging a plurality of shape elements which can be connected together in planar manner in a first region of a surface of the first part. The method moreover comprises application of a first adhesive layer onto the plurality of shape elements and in a second region of the surface of the first part. The method finally involves joining the first and second parts, the first adhesive layer being brought into contact with the surface of the second part. A corresponding apparatus is provided for joining parts which are subject to tolerance in the aerospace sector.

Abstract: A separating film with an anti-adhesion layer for preventing an adhesive connection between a thermally curable levelling compound, applied in the region of a joining zone of a first component, and a joining zone of a second component to be joined to the first component. The anti-adhesion layer is provided, at least in parts, with a heating layer. As a result of the actively electrically heatable heating layer of the separating film, which is an integral part of the separating film, the processing time for joining two components, which are subject to tolerances, using a thermally curable levelling compound (known as liquid shimming), can be reduced by at least 40% compared with the conventional process.

Abstract: A method for joining parts to be joined which are subject to tolerance in the aerospace sector. The method involves determining the geometric data of a first and second part to be joined, determining the joining gap dimensions of the first and second parts from the determined geometric data and arranging a plurality of shape elements which can be connected together in planar manner in a first region of a surface of the first part. The method moreover comprises application of a first adhesive layer onto the plurality of shape elements and in a second region of the surface of the first part. The method finally involves joining the first and second parts, the first adhesive layer being brought into contact with the surface of the second part. A corresponding apparatus is provided for joining parts which are subject to tolerance in the aerospace sector.

Abstract: The invention relates to a device for curing a plastic material, in particular a sealing compound and/or a filling compound for tolerance adjustment or gap filling, respectively, wherein the plastic material is at least partly inserted in a gap area between two components, and wherein at least one of the components is made of a fiber reinforced plastic material, in particular of a carbon fiber reinforced epoxy resin. According to the invention the device is provided with at least one electromagnetic inductor for a locally defined heating of the gap area and for curing the plastic material arranged in the gap area. Due to the electromagnetic inductor which might be a linear inductor or a circular inductor a contact-less and fast curing of the plastic material is possible.

Abstract: The present invention provides an assembly apparatus for supporting a fuselage section of an aircraft or spacecraft in an adjustable assembly position, with at least one stiffening bow for detachably stiffening the fuselage section and a rotational support, which rotatably supports the at least one stiffening bow. Also provided is a method for the assembly of a fuselage section of an aircraft or spacecraft in which an assembly position of the fuselage section is prescribed. In further steps, the fuselage section is reinforced with a stiffening bow and the stiffening bow is rotatably supported. The stiffening bow is then turned in such a way that the fuselage section rotates into the assembly position.

Abstract: A method for joining a first and a second component, at least one of which comprises a fibre-reinforced plastics material. The components are arranged in relation to one another in such a way that a gap region remains between the first and the second component. The gap region is filled, at least in portions, with an uncured plastics material filler in which nanoparticles are dispersed. Energy is introduced locally into the nanoparticles in order to cure the plastics material filler. In another aspect, the invention provides a device for joining two components.

Abstract: Disclosed is a holder for fixing all types of component, in particular lines, without using holes and largely without using tools inside a conventional fuselage structure of an aircraft with stringers and annular formers, the formers each being provided with an angle bracket at crossing points between a stringer and an annular former. The holder is configured so as to be split in two with a lower part and an upper part which can be connected thereto, the lower part being slidable onto an angle bracket. By attaching the upper part to the lower part, the holder is positionally fixed at the crossing point in the top region of an annular former. It is fixed in its final position by connecting the holder to a transverse line holder as a function element by means of an expansion pin or other connection elements.

Abstract: The invention relates to a device for curing a plastic material, in particular a sealing compound and/or a filling compound for tolerance adjustment or gap filling, respectively, wherein the plastic material is at least partly inserted in a gap area between two components, and wherein at least one of the components is made of a fiber reinforced plastic material, in particular of a carbon fiber reinforced epoxy resin. According to the invention the device is provided with at least one electromagnetic inductor for a locally defined heating of the gap area and for curing the plastic material arranged in the gap area. Due to the electromagnetic inductor which might be a linear inductor or a circular inductor a contact-less and fast curing of the plastic material is possible.

Abstract: Disclosed is a holder for fixing all types of component, in particular lines, without using holes and largely without using tools inside a conventional fuselage structure of an aircraft with stringers and annular formers, the formers each being provided with an angle bracket at crossing points between a stringer and an annular former. The holder is configured so as to be split in two with a lower part and an upper part which can be connected thereto, the lower part being slidable onto an angle bracket. By attaching the upper part to the lower part, the holder is positionally fixed at the crossing point in the top region of an annular former. It is fixed in its final position by connecting the holder to a transverse line holder as a function element by means of an expansion pin or other connection elements.

Abstract: The present invention provides an assembly apparatus for supporting a fuselage section of an aircraft or spacecraft in an adjustable assembly position, with at least one stiffening bow for detachably stiffening the fuselage section and a rotational support, which rotatably supports the at least one stiffening bow. Also provided is a method for the assembly of a fuselage section of an aircraft or spacecraft in which an assembly position of the fuselage section is prescribed. In further steps, the fuselage section is reinforced with a stiffening bow and the stiffening bow is rotatably supported. The stiffening bow is then turned in such a way that the fuselage section rotates into the assembly position.