Abstract: Provided is an aircraft fuselage structure having an outer skin, a support structure arrangement comprising a multiplicity of frame elements and a floor structure arrangement having a multiplicity of floor support struts. The aircraft fuselage structure provides a connection between the floor structure arrangement and the support structure arrangement which is as simple and quick to produce as possible, while not significantly increasing the weight or weakening the structure. Either the floor structure arrangement or the support structure arrangement can have at a connection there between a male connector element or a female connector element. The male connector element can have a peg which extends in the engagement direction and which has a circumferential outer surface which is provided with a multiplicity of circumferential projections. The female connector element can have a cavity, the inner surface of which is provided with a multiplicity of circumferential tabs.

Abstract: A fuselage segment of an aircraft fuselage is provided with an outer skin and an inner skin that are spaced apart from one another by a core, wherein conduits for system installations are integrated into the core, as well as a method for manufacturing such a fuselage segment.

Abstract: A method for producing and connecting fibre-reinforced components, in particular for an aircraft or spacecraft. The method includes the steps of: (a) providing a textile planar structure, of which merely a first sub-region is impregnated with a matrix; (b) heating the textile planar structure which is impregnated in part, in such a way that the matrix provided in the first sub-region of the textile planar structure cures; (c) connecting the textile planar structure in a second sub-region of the textile planar structure, different from the first sub-region, by stitching the second sub-regions; (d) introducing a further matrix at least into the stitched second sub-regions of the textile planar structure; and (e) heating the impregnated textile planar structure in such a way that the further matrix present in the stitched second sub-regions of the textile planar structure cures. The present invention further relates to aircraft or spacecraft production.

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: 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: 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: Disclosed are methods for firmly joining fiber-reinforced, plastic-based adherends, wherein depressions are introduced into opposing lateral surfaces of the adherends, and have injected into them a fiber-reinforced plastic material that serves as an adhesive, a device for implementing such a method, as well as a component joined in this way.

Abstract: Systems and methods for fabrication of composite shell elements and to the assembly of large scale structures comprising such composite shell elements are provided. The composite shell elements comprise two regions in which the resin is cured to different levels. As a consequence, the flexibility of the first region is greater than the flexibility of the second region. Since the first region defines a bending line, the composite shell element can be deformed along the bending line during assembly of the large scale structure. Thus, tolerances in fabrication of the composite shell elements may be compensated for in a time-efficient manner without the need for applying a shimming process.

Abstract: A fastening device which is suitable, in particular, for use in aircraft construction includes a carrier which is composed of a rollable or foldable material and has a first surface, intended for abutting against a component to be connected to the fastening device, and a second surface opposite the first surface. A plurality of openings are formed in the carrier and pass through the carrier. The fastening device also includes a plurality of heads, each provided with an internal thread, which are connected to the carrier or formed integrally with the carrier and which extend in such a manner from the second surface of the carrier that the internal threads of the heads are aligned with the openings passing through the carrier.

Abstract: A fastening arrangement for fastening a component, in particular a supply line, of an aircraft or spacecraft. The fastening arrangement includes a structural element of the aircraft or spacecraft; an adhesive retainer, which comprises a flexible connection portion having an adhesive surface for placing onto the structural element and a retaining portion, operatively connected to the connection portion, for receiving the component, at least in portions; and an adhesive material, which is arranged between the adhesive surface and the structural element. Also provided is an adhesive retainer of a fastening arrangement of this type, and an aircraft or spacecraft having a fastening arrangement of this type and/or an adhesive retainer of this type.

Abstract: The invention pertains to a fuselage segment (2) that extends in a longitudinal fuselage segment axis (A) and is closed in a circumferential direction (U) around this longitudinal fuselage segment axis, wherein the fuselage segment features: a plurality of shell components (4) for forming a skin of the fuselage segment (2) that respectively feature two first shell component edges (6) extending along a longitudinal shell component direction (LS) and two second shell component edges (10) extending along a lateral shell component direction (LB), wherein the shell components (4) are respectively connected to at least one adjacent shell component (4) along at least one first shell component edge (6) and along at least one second shell component edge (10), and wherein at least the direction of a tangent (T) on first shell component edges (6), on which two respective shell components (4) are connected to one another, and/or on second shell component edges (10), on which two respective shell components (4) are connec

Abstract: A connection device for a plurality of cabin components of an aircraft includes a rail extending in a longitudinal direction of an aircraft structure, wherein the plurality of cabin components is disposed on the rail; and a plurality of adjustment devices configured to self-adjust each of the plurality of cabin components in the longitudinal direction.

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: A method is provided for producing a bonded joint between fiber-reinforced thermoplastic parts to be joined, in which fiber-containing plastic material is mixed into the joining zone while friction stir welding the parts to be joined in the form of a butt joint. A device for carrying out such a method for a joined component is also provided.

Abstract: Disclosed are methods for firmly joining fiber-reinforced, plastic-based adherends, wherein depressions are introduced into opposing lateral surfaces of the adherends, and have injected into them a fiber-reinforced plastic material that serves as an adhesive, a device for implementing such a method, as well as a component joined in this way.

Abstract: In a method for manufacturing a shell, at least two shell sections are fabricated out of a composite fiber material, at least one compensation body of a plastically deformable material is secured to at least one limiting edge of at least one shell section, the shell sections are overlapped to form the shell, yielding flat seams between respectively adjacent shell sections. The at least one compensation body is arranged on at least one of the seams. In order to compensate for dimensional deviations in each overlap, the shape of the corresponding compensation bodies is changed, and the shells sections are joined together at the seams.

Abstract: Disclosed is a method for the installation of systems in an aeroplane fuselage 4, a device 2 with a rails system 14 for the execution of the method, and a freight loading system 50, which uses the rails system 14 as a guidance system for cargo 52, 54.

Abstract: A fuselage segment of an aircraft fuselage is provided with an outer skin and an inner skin that are spaced apart from one another by a core, wherein conduits for system installations are integrated into the core, as well as a method for manufacturing such a fuselage segment.

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: The invention relates to an aircraft comprising an insulation system for thermal and acoustic insulation. Said insulation system includes a cabin, an outer skin, a sound insulating unit, and a heat insulating unit. The sound insulating unit is designed to acoustically insulate the aircraft. The heat insulating unit is designed to thermally insulate the aircraft. The sound insulating unit and the heat insulating unit are arranged between the cabin and the outer skin.