Airbus Operations Gmbh

Stephan Hoetzeldt

Christian Thomas

Gerhard Penski

Oliver Schindler

An aircraft interior equipment component () with a frame () which comprises two rigid frame sections (-) and a joint (-) connecting the rigid frame sections (-) to one another, and with a sheetlike section () which is supported by the frame () and is formed by a flexible and/or foldable membrane () connected to the frame ().

Aircraft interior equipment component and aircraft interior equipment component system

A module for sealing an interface between compartments of a pressurized cabin of an aircraft. The module comprises a frame, a sheet and a rigid structure. The frame includes an opening surrounded by attachment surfaces. The frame is connected or connectable to a support structure of the aircraft. The sheet is attached to the attachment surfaces of the frame for sealing the at least one opening. The rigid structure is attached to the sheet within the frame without contacting the frame so that a displacement of the rigid structure relative to the frame induces tensile stress in the sheet between the frame and the rigid structure.

Module for sealing an interface inside an aircraft

A device for installing a lining panel in an aircraft. The installation device comprises a main beam having first and second sections and a hinge pivotably connecting a first end of the first and second sections such that the first section can be pivoted relative to the second section about an axis perpendicular to a longitudinal axis of the first section. A first beam is provided at a second end of the first section, movable relative to the first section along its longitudinal axis, and a second beam is provided at a second end of the second section, movable relative to the second section along its longitudinal axis. Also, a first longitudinal element connected to an end of the first beam facing away from the first section, and a second longitudinal element connected to an end of the second beam facing away from the second section are provided.

Installation device

A method of producing a panel for lining or cladding an aircraft interior, such as an aircraft cargo hold includes arranging at least one resin layer of a thermo-plastic polymer and at least one reinforcement layer of reinforcement fibers upon one another in a stack, wherein each resin layer extends adjacent and/or substantially parallel to each reinforcement layer; and consolidating the stack to form a panel by applying heat and pressure to the stack. The pressure is applied to the stack in a direction substantially perpendicular to a primary plane of the layers. The pressure is applied to the stack in a non-constant distribution over the primary plane. A corresponding panel for lining or cladding an aircraft interior, such as a cargo hold is also described.

Panel and method of producing same

The invention pertains to a composite panel with a first cover layer, a second cover layer and a first core layer that is arranged between the first cover layer and the second cover layer and features a plurality of cells that are separated from one another by walls at least in certain areas, wherein the first cover layer features a draining layer. The inventive composite panel may be distinguished from a composite panel according to the state of the art in that a second core layer with a plurality of cells that are separated from one another by walls at least in certain areas is arranged between the first cover layer and the first core layer.

Composite panel

A decompression device is provided having a frame element, in which at least one decompression opening is formed, and a cover is fastenable by means of a fastening device to the frame element in order in a first position to close the decompression opening formed in the frame element. The fastening device includes at least one holding clip and at least one receiving device that is complementary to the holding clip. The holding clip and the receiving device complementary to the holding clip are situated in engagement with one another when the cover is situated in its first position and are adapted to move out of engagement when a predetermined differential pressure acts upon the cover in order to enable the cover to move relative to the frame element into a second position, in which the cover releases the decompression opening formed in the frame element.

Decompression device and decompression system

An aircraft cabin panel for acoustic absorption in an interior space includes a core layer, a first cover layer and a second cover layer. The first cover layer includes a space-enclosing first surface, and the second cover layer is arranged opposite the first cover layer. The first cover layer is acoustically transparent, and the core layer includes a honeycomb core with a plurality of tubular or honeycomb-like cells that are open throughout the thickness of the honeycomb core. The honeycomb core on the face pointing towards the first cover layer extends parallel to the first cover layer so as to be continuously throughout, and on the face pointing towards the second cover layer comprises recesses which extend over several cells. Absorbers are accommodated in the recesses.

Growing community of inventors

Bremen, Germany

Stephan Hoetzeldt