Airbus Operations Gmbh

Airbus Deutschland Gmbh

Fraunhofer-Gesellschaft Zur Foerderung Der Angewandten Forschung E.V.

Rainer Müller

Ralf Schliwa

Nicholas E Brownjohn

Andreas Baatz

Christian Thomas

Marc Wesseloh

Norbert Staudigel

Robert Redecker

Benjamin Grenzing

Georg Mühlthaler

Peter Turanski

Dietmar Voelkle

Walter Kulcke

Florian Hesselbach

Wilko Oestereich

Stephan Risse

Thorsten Reinelt

Reinelt Thorsten

Tobias Lechner

Benjamin Joemann

Nicholas Brownjohn

A cladding element having a heating layer in a sandwich construction. In the case of a cladding element in a sandwich construction for an interior space of an aircraft, the cladding element includes a core layer and a first cover layer. The first cover layer forms a visible side of the cladding element. An electrically heating layer extends at least across a sub-face of the first cover layer and serves for generating heat for emission through the first cover layer is disposed between the core layer and the first cover layer.

Cladding element having a heating layer in a sandwich construction

A cabin lining element for an aircraft cabin which is arranged in the interior of an aircraft fuselage structure, having a fuselage structure side and a cabin side. The cabin lining element comprises an electrically contactable heating lacquer layer at least in regions on its fuselage structure side. A rib is provided for an aircraft fuselage structure, having at least one foot portion on the outer skin facing side and a cabin facing side head portion. The rib comprises an electrically contactable heating lacquer layer at least in regions on a side of the head portion facing the cabin. As a result of the heating lacquer layer, it is possible to omit insulation which otherwise surrounds the rib heads and, as a consequence, to enlarge the width of the cabin.

Cabin lining element for an aircraft cabin and rib for an aircraft fuselage structure

An internal cladding part for cladding a fuselage structure of an aircraft is disclosed having a first cover layer that extends in a planar manner, a second cover layer that extends in a planar manner, a core layer which is disposed between the first and the second cover layer and is connected to the first and the second cover layer and defines a receptacle cavity, and an insulation structure having a porous insulation core and an evacuated film sheath that encases the insulation core in a gas-tight manner. The insulation structure is disposed in the receptacle cavity between the first and the second cover layer.

Internal cladding part for cladding a fuselage structure of an aircraft

An insulation package for thermal and acoustic insulation of a vehicle cabin has a cutout to allow a fastening device to pass through. An insulating element that is disposed in an area of the insulation package surrounding the cutout has an opening corresponding to the cutout for allowing a fastening device to pass through. At least part of the insulating element is aligned perpendicularly to an axis of the passthrough in the cutout and conformed so as to create a gap between a fastening device that has passed through and the insulation package. In this way, condensed water may be prevented from passing through the cutout in the insulation package and into the aircraft cabin.

Condensed water decreasing insulation package for thermal and acoustic insulation of a vehicle cabin

The invention pertains to an insulation structure for thermally and acoustically insulating an aircraft that features at least one heavy layer, wherein the insulation structure according to the invention is characterized in that the insulation structure comprises an additional absorption layer, in that the heavy layer is perforated at least in certain areas, and in that the perforated area ratio of the heavy layer is adapted in such a way that the heavy layer is essentially transparent to sound for frequencies below a double-wall frequency of the insulation structure. This makes it possible to dampen sound with low frequencies below the double-wall frequency as effectively as possible.

Insulation design for thermal and acoustic insulation of an aircraft

A window arrangement is provided for enlarging a window area in an aircraft. The window arrangement includes, but is not limited to at least one first installation element. The at least one first installation element is designed to convey fluids, and furthermore includes, but is not limited to a transparent region which covers a first window region such that light waves in the visible spectrum can be let through.

Window arrangement for installing larger aircraft windows

When a fire breaks out, air flows that promote the spread of fire may occur in the region between the load bay and the skin of the aircraft. According to one embodiment of the present invention, a fire barrier is disclosed that allows rapid decompression of the passenger cabin in the normal operating mode of the aircraft and prevents flashovers in case of a fire. In this case, the fire barrier may be arranged at different positions in the intermediate wall space of the aircraft.

Fire barrier for an aircraft fuselage

The invention relates to an arrangement for lining the interior of a passenger vehicle such as an airplane including a honeycomb formation of several honeycombs arranged side by side. At its end, the honeycomb body is supported by a cover layer supported above and below the honeycomb formation such that by means of two cover layers glued onto the honeycomb formation, a layer design of the honeycomb paneling is created, which layer design is arranged so as to extend parallel to the outer skin of the aircraft and follow the curvature of the outer skin. The honeycomb formation used is made of paper or aramide honeycombs or of a mixed combination of both honeycomb types; on whose cross section of the honeycomb body a CFK cover layer is positioned to both ends of the honeycomb bodies. As an alternative, further CFK insulation layers are glued onto the outer surface of the respective cover layer supported above and below the honeycomb formation, which cover layers comprise a CFK or GFK. Moreover, the layer design of the honeycomb paneling may comprise further honeycomb formations which are additionally stacked on and glued to the honeycomb formation used.

Panel arrangement for an interior lining of a passenger cabin in an aircraft

Growing community of inventors

Rosengarten, Germany

Rainer Müller