Abstract: A connection arrangement for at least two abutting components to be firmly connected to one another, includes a self-piercing rivet having a rivet head for punching of a hole and subsequent riveting of the components, wherein a washer is allocated to the self-piercing rivet at the distal end region opposite to the rivet head, with the washer including a frontal area for the insertion of a circular indentation to create a firm compression connection between a hole in the washer and the distal end region of the self-piercing rivet.

Abstract: Disclosed are a method and a device for the connection of two components indirectly or directly in an overlap joint, wherein component sections located in the overlap are pressed together for each drilling procedure by means of a clamping unit formed from a pressure application device on the drilling machine side and a guide on the component side, such that any penetration of chips between the component sections is prevented and temporary connecting elements can be dispensed with.

Abstract: Disclosed is a method for the manufacture of an aircraft fuselage with at least two fuselage barrels wherein connecting segments are firstly prepared for the formation of a transverse joint region for a later transverse joint, and the fuselage barrels are then constructed around the connecting segments; also disclosed is an aircraft fuselage with ring-type connecting segments for the formation of such a transverse joint.

Abstract: A clamping device is provided for an assembly of a stringer coupling in a region of a lateral butt joint between a first and a second fuselage section of an aircraft for coaxially connecting a respective first and second stringer of the first and the second fuselage sections, the stringer coupling intersecting a frame element profile in the region of the lateral butt joint. A supporting yoke is configured to bridge the frame element profile in an arc-shaped manner and includes a first end foot supported by the stringer coupling on the first side of the frame element profile and a second end foot supported by the stringer coupling on the second side of the frame element profile. The supporting yoke includes a middle tensioning hook configured to interact with the frame element profile. The first and the second end feet are tensionable against the stringer coupling.

Abstract: The invention relates to a method for joining at least two aircraft fuselage segments (2, 3) by friction stir welding with a tool (8) generating friction heat for the partial plasticisation of an edge region (6, 7) of at least one of the two aircraft fuselage segments and a counter bearing (10) for absorbing the force exerted by the tool (8) on at least one of the two aircraft fuselage segments, wherein at least one of the two aircraft fuselage segments comprises at least one rib (17) and/or one stringer (16). In order to minimise the necessary expense incurred in association with the production aids for the FSW process, it is proposed that the at least one rib (17) and/or the at least one stringer (16) of the at least one aircraft fuselage segment (2, 3) should be used as a counter bearing (10).

Abstract: A method of fitting a fuselage shell of an aircraft with at least one window frame of a cabin window includes positioning an uncured laminate including a fiber-reinforced plastic-based composite material configured to form a fuselage shell on a mold surface. A window aperture is introduced into the laminate. A window frame including a fiber-reinforced plastic-based composite material is positioned on the laminate in a region of the window aperture. The laminate is cured under the action of pressure and temperature so as to connect the window frame with the laminate by a material bond.

Abstract: A device for positional fixation of a first fuselage section to be joined onto a second one in a butt-join region, the first fuselage section being planked with a first skin and the second fuselage section being planked with a second skin. The fuselage sections are temporary connectable by at least one clamping element in the butt-join region for carrying out a joining process. The clamping elements are each formed with a holder and a counter holder, wherein for example the holders are positioned exteriorly on the second skin while the counter holders are positioned interiorly on an interior side of the first skin opposite in the butt-join region. Each holder comprises at least one magnet for temporarily fixing the fuselage sections to one another and preventing intrusion of bore chips in-between the skins and/or, as the case may be, a butt-join strap by use of the magnetic force of attraction toward the counter holder.

Abstract: A device and method for the contactless and therefore non-destructive measurement of a degree of dryness of a coat of paint applied to a substrate. The device comprises at least one transmitter for electromagnetic radiation, at least one receiver for determining the absorption of the electromagnetic radiation radiated into the coat of paint, and a measuring means. In the measuring means, the raw measured values measured by the receiver are processed and the degree of dryness, calculated therefrom, of the coat of paint is displayed. Either microwave radiation or infrared radiation in the near infrared range is used as measuring radiation, at least one time-dependent measurement of the absorption at a constant wavelength being made in both cases. In addition, the invention relates to a method for determining the degree of dryness of a coat of paint by means of the device.

Abstract: A device for pretreating an exterior surface of an aircraft coated with an aircraft-specific base material so as to prepare the surface for a final painting with aircraft paint includes a pretreating tool. The pretreating tool has a laser head configured to activate the aircraft-specific base material using a laser. The device also includes a support construction including a robot device and a control unit configured to control and move the laser head over the surface using the robot device.

Abstract: An aircraft includes a fuselage having a painted exterior surface having a first color; a decorative film including plastic and having a second color different from the first color and adhesively bonded to the fuselage, wherein the decorative film includes at least one of a polyvinyl fluoride film, a polyester film, a polyvinyl chloride film, a polyethylene film, and a polypropylene film, wherein the decorative film is formable via one of polymerization, polyaddition and polycondensation; and a layer of clear paint containing a UV filter for erosion protection and covering the decorative film.

Abstract: A processing device for coating a surface of a rudder unit of an aircraft includes a plurality of spatially delimited work stations, wherein each of the plurality of work stations are disposed in succession and are configured to produce an assembly line-like coating process, wherein the plurality of work stations. The work stations include a pretreating station configured to activate the surface so as to form an activated surface; a painting station disposed downstream of the pretreating station and configured to paint the activated surface with at least one layer of paint having a first color so as to form a painted surface and configured to dry the painted surface immediately after the painting; and a decorating station.

Abstract: A device for painting a curved outer surface of an aircraft includes a paint applicator having a plurality of spray painting heads each assigned to one of a plurality of different base color supply units containing one of polyurethane aircraft paint and ink. The device further includes a spatially adjustable positioning device configured to move the paint applicator relative to the curved outer surface and at least one sensor device configured to determine a three-dimensional geometry of the curved outer surface. The device also includes a control unit configured to coordinate a movement of the positioning device with a paint output of the paint applicator, wherein the control unit is configured to alternately activate each of the plurality of spray painting heads so as to produce a picture motif so as to derive a two-dimensional driving geometry based on the three-dimensional geometry.

Abstract: The invention relates to a device comprising a base plate and a support for adjusting the height of an assembly, in particular of a galley module in an aircraft, without using tools. According to the invention, two opposing wedge bodies are arranged such that they can be displaced horizontally between the base plate and the support, the oppositely directed manual displacement of the two wedge bodies, when the lock levers have been raised, causes in the “adjusting position” a raising or lowering of the support for the height adjustment. The assembly is connected to the support, for example by a conventional screw connection through the attachment hole in the support. The device according to the invention allows a user to perform a simple and rapid height adjustment of an assembly arranged thereon, thereby greatly reducing the assembly effort required for prefabricated assemblies or modules in aircraft.

Abstract: A method for tolerance compensation in an overlap joint between a first and a second body section of adjacent fuselage rings includes introducing a plurality of holes into a first body section corresponding to a pattern of rivets; arranging the first and second body section in an overlapping configuration so as to form an overlap; injecting a filler mass through the plurality of holes into a gap formed in the overlap; and hardening the filler mass.

Abstract: A lightweight structure is disclosed, in particular a lightweight structure for an aircraft which is formed from a large number of components which can be joined together by weld joining processes. According to the invention, the lightweight structure has a component thickness which is increased corresponding to the loads in the joint region of the at least one welded joint compared to a thickness of the component outside the joint region.

Abstract: The invention relates to a method for joining at least two aircraft fuselage segments (2, 3) by friction stir welding with a tool (8) generating friction heat for the partial plasticisation of an edge region (6, 7) of at least one of the two aircraft fuselage segments and a counter bearing (10) for absorbing the force exerted by the tool (8) on at least one of the two aircraft fuselage segments, wherein at least one of the two aircraft fuselage segments comprises at least one rib (17) and/or one stringer (16). In order to minimise the necessary expense incurred in association with the production aids for the FSW process, it is proposed that the at least one rib (17) and/or the at least one stringer (16) of the at least one aircraft fuselage segment (2, 3) should be used as a counter bearing (10).