Abstract: An aircraft interior equipment component (10) with a frame (12) which comprises two rigid frame sections (14a-h) and a joint (16a-h) connecting the rigid frame sections (14a-h) to one another, and with a sheetlike section (18) which is supported by the frame (12) and is formed by a flexible and/or foldable membrane (20) connected to the frame (12).

Abstract: 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.

Abstract: 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.

Abstract: A fastening arrangement for fastening an aircraft interior-trim component to an aircraft structural element, including a pin, including a first coupling element having a bearing-contact face portion, wherein the first bearing-contact face thereof has an engagement projection provided to engage with an opening in the surface of the aircraft interior-trim component. An engagement surface of the bearing-contact face portion includes an engagement element arrangement and includes a spacer fixable relative to the aircraft structural element. An engagement face is provided with an engagement element arrangement and includes a through-bore. When the engagement surface of the coupling element is in bearing contact with an engagement face of the spacer, the coupling element and the spacer cannot be displaced with respect to each other in the plane of the engagement surface, and engagement of the engagement elements arrangement is possible in relative positions of the engagement surface and the engagement face.

Abstract: An aircraft comprising a fuselage, a wing attached thereto, a jet engine attached to the wing or to the fuselage and comprising a main engine and an accessory arrangement, and a heat recovery arrangement. The heat recovery arrangement comprises a heat exchanger arranged in an exhaust zone of the main engine such that heat can be exchanged between an exhaust gas stream exiting the main engine and a working fluid passed through the heat exchanger, an energy converting arrangement received in the fuselage and passed through by the working fluid, the energy converting arrangement comprising an energy source driven by the working fluid, and a pipe arrangement for recirculating working fluid between the heat exchanger and the energy converting arrangement. An aircraft is provided having reduced complexity and increased efficiency, and an energy recirculation line is provided for transmitting energy from the energy source to the accessory arrangement.

Abstract: Method for producing a workpiece from a composite material, comprising the steps of: providing an assembly or stack which is formed from a first metal plate, a composite material panel and a second metal plate, deforming the assembly in a machine tool and curing the composite material between the two metal plates outside of the machine tool. The composite material panel can comprise a fibre-reinforced plastics material, for example, and the metal plates can be formed as punched plates.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: The present invention concerns a composite plate (1) comprising a first cover layer (3), a second cover layer (5), and a core layer (7) arranged between the first and the second cover layers (3, 5) and having a plurality of cells (9) which are at least partially open towards the first cover layer (3) and which are separated from each other by walls as well as a method of draining such a composite plate (1). In order to provide such a composite plate (1) in which improved resistance to ingress of liquid or formation of liquid accumulations is guaranteed in a simple and continual fashion it is proposed that a draining layer (13) is provided in the first cover layer (3), wherein the cells (9) are at least partially covered by the draining layer (13).

Abstract: 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.

Abstract: 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 fibres 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.

Abstract: 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.

Abstract: A fastening arrangement for fastening an aircraft interior-trim component to an aircraft structural element, including a pin, including a first coupling element having a bearing-contact face portion, wherein the first bearing-contact face thereof has an engagement projection provided to engage with an opening in the surface of the aircraft interior-trim component. An engagement surface of the bearing-contact face portion includes an engagement element arrangement and includes a spacer fixable relative to the aircraft structural element. An engagement face is provided with an engagement element arrangement and includes a through-bore. When the engagement surface of the coupling element is in bearing contact with an engagement face of the spacer, the coupling element and the spacer cannot be displaced with respect to each other in the plane of the engagement surface, and engagement of the engagement elements arrangement is possible in relative positions of the engagement surface and the engagement face.

Abstract: An aircraft interior equipment component (10) with a frame (12) which comprises two rigid frame sections (14a-h) and a joint (16a-h) connecting the rigid frame sections (14a-h) to one another, and with a sheetlike section (18) which is supported by the frame (12) and is formed by a flexible and/or foldable membrane (20) connected to the frame (12).

Abstract: 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.

Abstract: 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.

Abstract: The present invention relates to an aircraft cabin panel for sound reduction in an interior space. The invention in particular also relates to an aircraft comprising an interior lining with sound-absorbing and sound-reducing panels. In order to provide a panel that is optimized in terms of the design space required by it and in terms of its weight, for use in aircraft, which panel provides improved sound reduction and sound absorption characteristics, an aircraft cabin panel for sound reduction in an interior space is provided, which aircraft cabin panel in at least one region comprises a sandwich construction with a core layer, a first covering layer and a second covering layer. The core layer comprises sound absorbing open-pore core material. The first and the second covering layer are connected to the core layer in a planar fashion. The first covering layer is arranged towards the sound waves to be absorbed and the second covering layer is arranged opposite the first covering layer.

Abstract: A sandwich element for sound-absorbing inner cladding of means of transport, especially aircraft, comprising a three-dimensionally constructed core disposed between two substantially parallel cover layers is provided. Sound transmission passages are incorporated in the core, and/or in at least one cover layer. At least one sound absorption layer is in the area of a cover layer at least in parts. Passages in the cover layers and core provide good sound absorption and heat insulation. The passages allow transmission of sound. The through channels and the preferably inclined installation of the sandwich element allow foreign bodies to be flushed out by, for example, a cleaning liquid or condensation. Possibly sufficient sound absorption can be achieved without the sound absorption layer. Ventilation of the core prevents the long-term presence of condensation, which could cause corrosion and/or rotting. A fire-retardant layer including metal particles may increase fire protection and electromagnetic insulation.

Abstract: A sound absorption element for means of transport, in particular for aircraft, comprising at least one sound absorption panel arranged on a base panel with the base panel comprising a multitude of recesses, in particular a hole grid or the like, for the transmission of sound. According to the invention, the sound absorption panels are each framed by a frame, wherein on the at least one frame at least in some sections a transition profile, in particular to prevent fatigue fractures due to stepwise changes of rigidity between the at least one frame and the base panel is arranged. Due to the base panel comprising a multitude of recesses, in particular comprising a hole grid, in connection with the sound absorption panels an air-permeable sound absorption element can be achieved.