Abstract: A piston for an internal combustion engine includes a piston upper part and a piston lower part having a cooling channel including at least one inlet opening. A dam-type elevation is formed in the region of the at least one inlet opening through forging of the dam elevation in the cooling channel portion in the piston lower part. In one example, a funnel-shaped inlet contour is formed in the inlet opening by pre-forging. In one example, a V-shaped element is formed in the piston upper part cooling chamber portion in alignment with the inlet opening and used as a coolant jet splitter.

Abstract: A service box for storing in a storage rack arrangement of a cargo container of a vehicle, in particular an aircraft, including a rectangular bottom wall, a rectangular upper wall, side walls and narrow end walls and forms an interior space adapted to receive a trolley for catering goods. The service box is provided with a door at at least one of its narrow ends, the door forming at least the main part of the narrow wall and in the open state permits insertion and removal of the trolley and in the closed state provides for an essentially closed space for the trolley.

Abstract: A lift apparatus for transporting objects between compartments of an aircraft through an aperture in a floor structure separating the compartments and an aircraft in which such lift apparatus is mounted. The lift apparatus includes a conveyor with a retaining portion to selectively retain and release objects to be transported, a guide to which the conveyor is mounted to be linearly movable along a predetermined path of motion defined by the guide, and a moving mechanism for driving the conveyor to linearly move along the predetermined path of motion. The retaining portion and a closing portion of the conveyor are along the path of motion, and the lift apparatus mounts in an aircraft with the path of motion extending through the aperture. The conveyor is selectively movable along the predetermined path of motion between positions.

Abstract: A floor assembly for an aircraft comprising a multiplicity of supports configured to be fastened in pairs to opposite sides of a frame of the aircraft, and a monolithic self-supporting floor element comprising at least two longitudinal members, a floor plate arranged on the longitudinal members and a respective connecting element arranged at each end of each of the longitudinal members. The floor element can be fastened to the frame by fastening of each connecting element to a corresponding support, and the floor plate can extend in the direction of the longitudinal members at least between two supports fastened in pairs. Furthermore, an aircraft region comprises such a floor assembly, an aircraft comprises such an aircraft region.

Abstract: A luggage compartment for installation on the fuselage or ceiling in a vehicle, in particular aircraft, comprises at least two side walls which are connectable in load-bearing fashion to a primary structure of the vehicle and which have a fiber composite structure. The fiber composite structure is produced from reinforced curable molding compound and has at least one reinforcement element at least partially embedded therein. The luggage compartment furthermore comprises a shell element which is connected to the side walls and which defines at least a part of a stowage space of the luggage compartment.

Abstract: A functional arrangement in a cabin of a vehicle includes a monument with a housing having several side walls, which define an interior space, and at least two adjacently arranged seats each having a backrest and headrest. The seats adjoin an exterior side of a first side wall of the housing, and have a seating direction facing away from the first side wall. The first side wall includes a first surface portion that is located at least sectionally behind the headrests of the at least two seats in a vertical direction and includes at least one bulge extending at least in a horizontal direction between two adjacently lying headrests. At least one piece of equipment is situated in the interior space, extends into the at least one bulge and is usable in the interior space of the monument.

Abstract: A lining panel having a panel element, a rectangular through hole and a flap is provided. The lining panel has a flap which is rotatable about a hinge integrated into the panel element in order to open and/or close the rectangular through hole. A fuselage element for an aircraft includes such a lining panel.

Abstract: A method for producing a fiber composite component includes a step (a) that includes a production of a semi-finished product by: providing a core layer having cavities; covering an outer face of the core layer with a layer-shaped semi-finished product having continuous fibers pre-impregnated with a first duroplastic matrix material; and applying a molding compound to a first deposit area of a front face of the first semi-finished product, the front face facing away from the core layer, wherein the molding compound includes a second long-fiber-reinforced duroplastic matrix material. The method also includes a step (b) for extruded reshaping of the semi-finished product to the fiber composite component. The extruded reshaping is performed at an operating temperature, and the first and the second matrix material are configured such that flowability of the second matrix material is higher than flowability of the first matrix material during the reshaping.

Abstract: A method for manufacturing an overhead storage compartment for an aircraft cabin, including providing a shell part extending between a first end and a second end, wherein the shell part has a first edge at the first end and a second edge at the second end. A first end wall and a second end wall are provided. The shell part and the first and second end walls are assembled, wherein the first edge is attached to the first end wall and the second edge is attached to the second end wall, such that the shell part, the first end wall and the second end wall together surround an interior space. An object, to provide a simple and fast method for manufacturing an overhead storage compartment, wherein possibly little handwork is required, is achieved in that the first end wall and/or the second end wall include an undirected long fiber reinforced plastic material.

Abstract: An aircraft monument for installation in an aircraft cabin. The aircraft monument comprises a movable side wall that is configured for separating the aircraft monument from a passenger area of the aircraft cabin, and that is configured for being moved. The aircraft monument further comprises at least one seat that is fastened to the movable side wall. Also disclosed is an aircraft area having a main aisle that extends along a longitudinal axis of an aircraft cabin, and having an aircraft monument situated next to the main aisle. Also disclosed is an aircraft that includes at least one aircraft area.

Abstract: An insulation component to be attached to a fuselage structure of an aircraft. The insulation component extends in a planar manner, and at least one peripheral recess, running transversely to the at least one longitudinal recess, is formed in a first surface of the insulation component configured to receive a respective associated peripheral support of the fuselage structure.

Abstract: An aircraft interior fitting component system comprising an aircraft interior fitting component, a support element attached to the aircraft interior fitting component, and an aircraft primary structure component. The support element is dimensioned in such a way and is attached to the aircraft interior fitting component in such a position that, in an assembled state of the aircraft interior fitting component in an aircraft, it is supported on the aircraft primary structure component at least when a predetermined load acts on the aircraft interior fitting component along the x-axis of the aircraft in flight direction.

Abstract: An aircraft interior lining component is formed at least partially of a thermoplastic foam material and includes a first surface which faces an interior of an aircraft cabin when the aircraft interior lining component is mounted in an aircraft, and a second surface which faces away from the interior of the aircraft cabin when the aircraft interior lining component is mounted in an aircraft. The second surface of the aircraft interior lining component includes at least one supporting section and at least one surface section adjacent to the supporting section and recessed relative to the supporting section. The supporting section is dimensioned and arranged so that it is supported, when the aircraft interior lining component is mounted in an aircraft, on an element of a primary structure of the aircraft at least when a predetermined load acts on the first surface of the aircraft interior lining component.

Abstract: A lift apparatus for transporting objects between compartments of an aircraft through an aperture in a floor structure separating the compartments and an aircraft in which such lift apparatus is mounted. The lift apparatus includes a conveyor with a retaining portion to selectively retain and release objects to be transported, a guide to which the conveyor is mounted to be linearly movable along a predetermined path of motion defined by the guide, and a moving mechanism for driving the conveyor to linearly move along the predetermined path of motion. The retaining portion and a closing portion of the conveyor are along the path of motion, and the lift apparatus mounts in an aircraft with the path of motion extending through the aperture. The conveyor is selectively movable along the predetermined path of motion between positions.

Abstract: A cargo unit for storage in a cargo hold of an aircraft including a housing and a storage rack arrangement, the housing enclosing the storage rack arrangement and including a transport opening. The cargo unit is connectable to a transport arrangement operable for removing objects from the storage rack arrangement and placing objects in the storage rack arrangement through the transport opening when the cargo unit is arranged in an operating position. The cargo unit includes a transport cover movable between a closed position where the transport cover closes the transport opening and an opened position where the transport opening is not covered by the transport cover. The transport cover is adapted to be only movable from its closed position to its opened position after engagement with a transport arrangement. A lower deck catering system including a cargo unit and a transport arrangement is described.

Abstract: A service box for storing in a storage rack arrangement of a cargo container of a vehicle, in particular an aircraft, including a rectangular bottom wall, a rectangular upper wall, side walls and narrow end walls and forms an interior space adapted to receive a trolley for catering goods. The service box is provided with a door at at least one of its narrow ends, the door forming at least the main part of the narrow wall and in the open state permits insertion and removal of the trolley and in the closed state provides for an essentially closed space for the trolley.

Abstract: A locking mechanism, in particular suitable for use in a decompression arrangement, includes a pressure chamber surrounded by a delimiting wall, wherein at least a section of the pressure chamber delimiting wall is formed by an actuating element which is in a rest position when the pressure in the interior of the pressure chamber corresponds to the ambient pressure and moves into a differential pressure position when the pressure in the interior of the pressure chamber exceeds the ambient pressure by a predetermined differential value. The locking mechanism further includes a locking bar which is kept in a locked position when the actuating element is in its rest position and is movable into an unlocked position when the actuating element is in its differential pressure position.

Abstract: A passenger monitoring and directing system for use in an aircraft cabin is provided. This system includes at least one information unit to be arranged in the aircraft cabin and at least one passenger monitoring device. The information unit includes at least one monitoring portion and the passenger monitoring device is assigned to the information unit and arranged relative to its monitoring portion in order to monitor the passengers through the monitoring portion of the information unit.

Abstract: A decompression assembly (10; 10?) for an aircraft comprises a first cabin lining element (12; 12?) having a boundary area (14; 14?) and a second cabin lining element (20; 20?) having a boundary area (22; 22?), wherein the boundary area (22; 22?) of the second cabin lining element (20; 20?) is disposed at a smaller distance from an aircraft outer skin (24; 24?) than the boundary area (14; 14?) of the first cabin lining element (12; 12?). An air discharge opening (28; 28?) is disposed between the boundary area (14; 14?) of the first cabin lining element (12; 12?) and the boundary area (22; 22?) of the second cabin lining element (20; 20?) for discharging air from a cabin (18; 18?) of the aircraft into an area (30; 30?) of the aircraft located between the cabin lining elements (12, 20; 12?, 20?) and the aircraft outer skin (24; 24?).

Abstract: A covering device includes a sealing element and a rib structure which is disposed on a surface of the sealing element. The rib structure includes a plurality of ribs which extend parallel to the surface of the sealing element, wherein the bendability of the ribs parallel to the surface of the sealing element is high, and perpendicular to the surface of the sealing element is low.