Airbus Operations Gmbh

Steffen Biesek

Robert Alexander Goehlich

Holger Frauen

Rolf Bense

Marco Pacchione

Cihangir Sayilgan

Christian Kulik

Michael Kreimeyer

Dirk Groβ

Karl-Hinrich Herbst

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.

Fuselage cell for an aircraft, particularly an airplane

An aircraft includes an insulation system for thermal and acoustic insulation. The 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.

Aircraft comprising an insulation system for thermal and acoustic insulation

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.

Method for producing large-sized shell segments as well as shell segment

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.

Lightweight structure

The invention relates to a method for joining at least two aircraft fuselage segments () by friction stir welding with a tool () generating friction heat for the partial plasticisation of an edge region () of at least one of the two aircraft fuselage segments and a counter bearing () for absorbing the force exerted by the tool () 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 () and/or one stringer (). 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 () and/or the at least one stringer () of the at least one aircraft fuselage segment () should be used as a counter bearing ().

Growing community of inventors

Hamburg, Germany

Steffen Biesek