Abstract: A processing device for the assembly of an aircraft encompasses a positioning frame, a guide device and a movable tool arm. The positioning frame can be attached to a segment of a hall floor. The guide device is movably guided on the positioning frame. The movable tool arm is attached to the guide device, and its free end exhibits a tool holder. The processing method for the assembly of aircraft encompasses the steps of providing a positioning frame on a segment of the hall floor, and guiding a guide device on the positioning arm. The guide device here exhibits a movable tool arm, and a free end of the tool arm exhibits a tool holder.

Abstract: A method for the assembly of an aircraft fuselage, to a fuselage manufacturing station and to a construction kit includes providing a pre-assembled cockpit unit, a pre-assembled wing box, a pre-assembled tail unit and a plurality of pre-fabricated fuselage shell segments. Furthermore, the method involves positioning the cockpit unit, the wing box and the tail unit. Moreover, a first front fuselage shell segment is positioned on a front connecting region of the wing box, and a first rear fuselage shell segment is positioned on a rear connecting region of the wing box. The first front fuselage shell segment is joined to a second front fuselage shell segment, and the first rear fuselage shell segment is joined to a second rear fuselage shell segment. As a result of the above, following the assembly of the aircraft fuselage an aircraft fuselage can be provided that already comprises equipment elements or functional elements.

Abstract: A fuselage cell for an aircraft includes at least two shell segments forming a fuselage cell. The shell segments are provided with a plurality of longitudinal and/or circumferential reinforcements that are integral with a skin panel of the respective shell segment. The reinforcements at least sectionally form a closed cross-sectional geometry together with at least the skin panel of the corresponding shell segment in order to create at least one hollow space, wherein at least one system component at least sectionally extends and/or at least one system medium is at least sectionally routed in the at least one hollow space. The reinforcements also fulfill the function of accommodating at least part of the system components and system mediums of the technical equipment of the aircraft. This results in weight savings and a simplified installation because the number of required mountings and connectors for the system components is reduced.

Abstract: A riveting device for the riveting of components in an overlap joint, with an upper tool for driving a rivet into a rivet hole passing through the components, and with a lower tool as a dolly, which has a deforming section for purposes of plastically deforming the end of a rivet shaft driven through the rivet hole, wherein the riveting device has a magazine with a feed device for purposes of feeding a rivet into a shot passage of the upper tool, an actuator for purposes of accelerating the rivet introduced into the shot passage of the upper tool in the direction of the components, and an adjustment system for purposes of aligning the shot channel with the rivet hole. Also disclosed is a method for the riveting of components in an overlap joint.

Abstract: A processing device for the assembly of an aircraft encompasses a positioning frame, a guide device and a movable tool arm. The positioning frame can be attached to a segment of a hall floor. The guide device is movably guided on the positioning frame. The movable tool arm is attached to the guide device, and its free end exhibits a tool holder. The processing method for the assembly of aircraft encompasses the steps of providing a positioning frame on a segment of the hall floor, and guiding a guide device on the positioning arm. The guide device here exhibits a movable tool arm, and a free end of the tool arm exhibits a tool holder.

Abstract: The application of a spraying agent by a spray device, the use of a spray device of this kind for spraying a component of an aircraft, and a method for displaying a region on a component to be sprayed. An embodiment of the spray device includes a spray unit and a light projection unit. The light projection unit is configured to project light onto a component to be sprayed as a function of at least one parameter of a spraying procedure that may be performed via the spray unit, in such a way that a resulting projection of light onto the component to be sprayed displays a region of the component to be sprayed which is sprayed during performance of the spraying procedure, using the at least one parameter.

Abstract: Speech communication on board a transport device. In particular, a method for adapting speech data serving for speech communication on board a transport device, to a computer program for executing the method, to a device for adapting speech data serving for speech communication on board a transport device, and also to a transport device with a device of such a type. An embodiment of the method for adapting speech data serving for speech communication on board a transport device comprises: obtaining information relating to at least one tone property, the information relating to the at least one tone property having been derived from recorded speech data appertaining to a person; and adapting speech data appertaining to the person and serving for speech communication on board the transport device on the basis of the obtained information about the at least one tone property.

Abstract: A method for adhesive application in vehicle construction during joining of joining partners which are subject to tolerances comprises the following steps: detecting the geometric data of the joining partners in an automated manner, detecting the joint gap dimensions of the joining partners from the detected geometric data, joining the joining partners in the joining position thereof, and applying the adhesive in the joint gap.

Abstract: A method for the assembly of an aircraft fuselage, to a fuselage manufacturing station and to a construction kit includes providing a pre-assembled cockpit unit, a pre-assembled wing box, a pre-assembled tail unit and a plurality of pre-fabricated fuselage shell segments. Furthermore, the method involves positioning the cockpit unit, the wing box and the tail unit. Moreover, a first front fuselage shell segment is positioned on a front connecting region of the wing box, and a first rear fuselage shell segment is positioned on a rear connecting region of the wing box. The first front fuselage shell segment is joined to a second front fuselage shell segment, and the first rear fuselage shell segment is joined to a second rear fuselage shell segment. As a result of the above, following the assembly of the aircraft fuselage an aircraft fuselage can be provided that already comprises equipment elements or functional elements.

Abstract: A method for joining, by adhesive bonding, at least two large joining partners in vehicle construction, in particular in aircraft construction, comprises the following steps: detecting the geometric data of the joining partners in an automated manner, detecting the joint gap dimensions of the joining partners from the geometric data, applying adhesive to one or both joint faces of the two joining partners to be joined as a function of the joint gap dimensions, joining the joining partners in the joining position, and sequentially applying joining pressure to the joint faces along the joint gap to bring the joining partners into the final joining position.

Abstract: A riveting device for the riveting of components in an overlap joint, with an upper tool for driving a rivet into a rivet hole passing through the components, and with a lower tool as a dolly, which has a deforming section for purposes of plastically deforming the end of a rivet shaft driven through the rivet hole, wherein the riveting device has a magazine with a feed device for purposes of feeding a rivet into a shot passage of the upper tool, an actuator for purposes of accelerating the rivet introduced into the shot passage of the upper tool in the direction of the components, and an adjustment system for purposes of aligning the shot channel with the rivet hole. Also disclosed is a method for the riveting of components in an overlap joint.

Abstract: In accordance with the method, an inside layer of a fuselage section skin made from first fibers is placed on a manufacturing surface, the first fibers being placed in one or more first fiber directions. On the inside layer, a stiffening structure is formed from stiffening fibers, the stiffening fibers being placed in one or more stiffening fiber directions. An outside layer of the fuselage section skin, comprising fourth fibers, is placed on the stiffening structure formed from stiffening fibers, the fourth fibers being placed in one or more fourth fiber directions. The stiffening structure is designed and developed in such a way that the fuselage section does not require an additional stiffening structure, is connected with the fuselage section skin, and comprises the inside layer, the stiffening structure, and the outside layer; in particular, an additional stiffening structure in the form of stringers and frames is not required.

Abstract: The subject matter herein discloses a method for producing a fuselage section of an aircraft via large-sized, in particular long, shell segments. The method includes joining at least two skin segments to form a large-sized skin field, welding a plurality of integral stringers onto the skin field, and welding a plurality of integral and closed ring frames to the skin field.

Abstract: A passenger supply arrangement provides a communications system and comfort system for a passenger of an aeroplane. The passenger supply arrangement includes a presentation surface configured to be integrated into a backrest of a passenger seat of an aeroplane and a passenger supply module configured to be disposed above the passengers seats of the aeroplane. The passenger supply module includes at least one projector configured to project an image onto the presentation surface. The image includes a monitoring area for playback of video and an operating area for displaying and for actuation of operating elements of the passenger supply module.

Abstract: Method and arrangement for supplying essentially hollow bodies with equipment wherein the hollow bodies each have a transverse dimension and a longitudinal dimension being larger than the transverse dimension. The bodies have at least one opening for accessing their interior from outside along their longitudinal dimension. The hollow bodies are arranged essentially side-by-side along the longitudinal dimension and they are moved along their transverse dimension in a clocked fashion. An arrangement comprises a plurality of conveyor means for moving hollow bodies, wherein the conveyor means are arranged such that the hollow bodies are arranged side-by-side along their longitudinal dimension and moved along their transverse dimension in a clocked fashion.

Abstract: The invention relates to a method for producing at least one fuselage cell of an aircraft with the following steps: at least partial production of surface protection and thermal insulation in the region of the at least one shell part, at least partial introduction of technical outfitting systems 1-3, 10-12, 22-24, 46-48, in particular of electrical and hydraulic lines, air-conditioning lines, electrical and hydraulic appliances, sanitary and catering equipment or the like, into the at least one shell part and/or the at least one floor grid 13, 41, and assembly of the at least one shell part and of the at least one floor grid 13, 41 into the at least one fuselage section 32.

Abstract: A shielding arrangement for the lightning protection of electrical lines and components in an aircraft includes a protected installation space for receiving the lines that is arranged in the region of a floor framework, at least one delimiting surface of the installation space being provided at least in certain regions with an electrically conductive shielding, the at least one delimiting surface of the installation space being formed with at least one floor panel and a further delimiting surface of the installation space being formed with at least one ceiling panel.

Abstract: A device and method for joining and tacking several individual components independently of shape and/or size to form inherently rigid, transportable sections for transportation vehicles, such as an aircraft is disclosed. According to one embodiment of the invention, the individual components may be spatially positioned relative to each other independently of shape and/or size. The spatial positions of the individual components may be determined by a measuring device, such as a laser measuring device, and varied via several positioning devices until a preset spatial position of the individual components has been reached in which the individual component are tacked together to form a section. In another embodiment, the positioning devices may be designed as base positioners, a first lateral positioner, a second lateral positioner, an upper positioner as well as an inner positioner.

Abstract: A method for adhesive application in vehicle construction during joining of joining partners which are subject to tolerances comprises the following steps: detecting the geometric data of the joining partners in an automated manner, detecting the joint gap dimensions of the joining partners from the detected geometric data, joining the joining partners in the joining position thereof, and applying the adhesive in the joint gap.

Abstract: A method for joining, by adhesive bonding, at least two large joining partners in vehicle construction, in particular in aircraft construction, comprises the following steps: detecting the geometric data of the joining partners in an automated manner, detecting the joint gap dimensions of the joining partners from the geometric data, applying adhesive to one or both joint faces of the two joining partners to be joined as a function of the joint gap dimensions, joining the joining partners in the joining position, and sequentially applying joining pressure to the joint faces along the joint gap to bring the joining partners into the final joining position.