Abstract: Additive manufacturing systems and methods having an extrusion head with a nozzle. The nozzle extrudes a composite material from an orifice of the nozzle to form a layer of a component. The composite material has at least a matrix material and a reinforcing material. The nozzle extrudes the matrix and reinforcing materials from the orifice simultaneously. The width and height of the orifice are adjustable to control the width and thickness of the layer extruded therefrom. The width and thickness of the layer are the same as the width and height, respectively, of the nozzle orifice, while the nozzle is extruding the composite material through the orifice. The width and height of the nozzle orifice are perpendicular to each other and transverse to an extrusion direction from the nozzle orifice. A majority of a surface area of the reinforcing material is encapsulated within the matrix material after being dispensed from the nozzle.

Abstract: A system for making a component having a plurality of layers sequentially deposited via additive manufacturing has a nozzle and a print controller. The nozzle has an orifice. The print controller defines a print pattern for the nozzle for each layer of the component. The print pattern defines a print order in which filaments are deposited from the nozzle to form one of the plurality of layers of the component. A cutter at the orifice of the nozzle is used to cut the filament as required according to the print pattern. The nozzle moves according to the print pattern for the layer of the component being formed and simultaneously coextrude an elastomeric matrix material and a reinforcing material from the orifice of the nozzle as one of the filaments, such that the reinforcing material is entirely internal to the elastomeric matrix material.

Abstract: An interior aircraft section having a cover for a gap between a lining and a monument. The cover comprises a basic body, at least one mounting end configured to be fixedly mounted to the monument, and a connector configured to fixedly mount the basic body to the lining. The connector is arranged in an area of the basic body overlapping the lining. Also, an aircraft having such interior aircraft section.

Abstract: A transition for a sidewall and a monument in an aircraft. The transition comprises a transition wall bridging a gap between the sidewall and the monument, a side fitting arranged at a side edge of the transition wall facing the sidewall, the side fitting being configured to overlap and/or mate the sidewall, and a mount attached to the transition wall and configured to be mounted to the monument.

Abstract: An aircraft system component carrier system includes at least one aircraft system component carrier module, at least one aircraft system component that is fastened via an aircraft system component holder to the aircraft system component carrier module, and an aircraft structural element of a fuselage upper shell, to which element the aircraft system component carrier module is fastened via a structural holder in such a way that the aircraft system component carrier module, the aircraft system component and the aircraft structural element form an assembly group that is capable of being handled independently.

Abstract: An aircraft system component carrier module includes a carrier element which is arc-shaped at least in sections and is configured, when the module is mounted in an aircraft, to extend at least in some sections substantially in the direction of the ribs of an aircraft structure over at least a section of a crown area of an aircraft cabin. The module includes a transverse carrier element which is configured, when the module is mounted in an aircraft, to extend in the crown area of an aircraft cabin substantially perpendicularly to a longitudinal axis of the cabin. The module further includes a structure holder for fastening the module to the aircraft structure, an aircraft system component holder for fastening at least one of the aircraft system components to the module and an attaching device, connected to the transverse carrier element, for attaching an aircraft luggage compartment to the module.

Abstract: An interior component carrier system for use in assembly of aircraft interior components in an aircraft includes a retaining system with at least one retaining element. A first connection device for connecting the retaining element to a first aircraft interior component and a second connection device are provided on the retaining element. On the retaining element a structural retainer is provided for fastening the retaining element to an aircraft structure. The interior component carrier system includes a hinge connectable to a second and a third aircraft interior component such that the third aircraft interior component is pivotable about a longitudinal axis of the hinge relative to the second aircraft interior component. The second connection device mounted on the retaining element is configured to be connected to the hinge and/or to a region of the second or third aircraft interior component, that is adjacent to the hinge.

Abstract: An aircraft insulation system comprising a foil extending at a distance from an inner surface of an aircraft outer shell. An air gap is defined between the foil and the aircraft outer shell. A cabin exhaust air duct is arranged adjacent to an inner surface of the foil and being adapted to have cabin exhaust air flow through the duct.

Abstract: A transport device for use when mounting interior component modules in an aircraft includes an undercarriage and an interior component module carrier unit. The interior component module carrier unit is supported on the undercarriage and is adapted to be connected to an interior component module, which is preassembled outside of the aircraft, in order to transport the interior component module with the aid of the transport device into a final assembly position in an aircraft fuselage element. At least a part of the interior component module carrier unit is movable relative to the undercarriage such that an interior component module connected to the interior component module carrier unit is movable horizontally and vertically relative to the undercarriage.

Abstract: The structural element of an aircraft fuselage, with stringers running in the longitudinal direction of the aircraft fuselage and ribs running transversely to the stringers in the circumferential direction of the fuselage. According to the invention, at least one of the stringers running in the longitudinal direction of the aircraft fuselage is designed as a fastening rail for elements to be installed in the aircraft fuselage.

Abstract: An apparatus for affixing an object to a rail includes, but is not limited to at least one base body, at least one locking body and at least one operating element. The locking body is held so as to be movable relative to the base body and is connected to the operating element by way of at least one bearing. The operating element is arranged so as to be rotatable in the base body, includes, but is not limited to a cam that acts on the base body, and when rotated moves the locking body towards the base body. In this way apparatus is created which makes possible the manual affixing and undoing, without the need for tools, of an object on and from a rail, for example, if needed, in order to reposition displaceable monuments in a cabin of an aircraft.

Abstract: The invention relates to a method for fastening an element of airplane interior equipment to a supporting structure in an airplane, comprising the steps of connecting the element of the airplane interior equipment to a first fixing device by using a first locking device, pivoting the element of the airplane interior equipment relative to the supporting structure, and connecting the element of the airplane interior equipment to a second fixing device by using a second locking device. Thus the element of the airplane interior equipment is fastened relative to the supporting structure.

Abstract: A shell structure of a fuselage comprising a plurality of ribs arranged in predetermined intervals. An outer skin is fastened to each of the plurality of ribs. A plurality of fastening devices is coupled to the outer skin between the ribs and facing inwards into the fuselage. An interior structural element is mounted to the outer skin in a load transmitting manner using the fastening devices.

Abstract: An energy absorber for aircraft, which includes one or more energy absorber elements and a housing, whereby the energy absorber elements can absorb crash impulses by plastic deformation within the housing. Thus, the load on the primary structure and the respective inboard devices is limited, which can lead to an increased, passive safety of the passengers and a weight reduction.

Abstract: A force level control for an energy absorber is provided for aircraft, and includes an adjustment element and a housing, whereby via the adjustment element, a bending radius of the energy absorber element is continuously adjustable in the housing.

Abstract: An aircraft system component carrier module includes a carrier element which is arc-shaped at least in sections and is configured, when the module is mounted in an aircraft, to extend at least in some sections substantially in the direction of the ribs of an aircraft structure over at least a section of a crown area of an aircraft cabin. The module includes a transverse carrier element which is configured, when the module is mounted in an aircraft, to extend in the crown area of an aircraft cabin substantially perpendicularly to a longitudinal axis of the cabin. The module further includes a structure holder for fastening the module to the aircraft structure, an aircraft system component holder for fastening at least one of the aircraft system components to the module and an attaching device, connected to the transverse carrier element, for attaching an aircraft luggage compartment to the module.

Abstract: An aircraft system component carrier system includes at least one aircraft system component carrier module, at least one aircraft system component that is fastened via an aircraft system component holder to the aircraft system component carrier module, and an aircraft structural element of a fuselage upper shell, to which element the aircraft system component carrier module is fastened via a structural holder in such a way that the aircraft system component carrier module, the aircraft system component and the aircraft structural element form an assembly group that is capable of being handled independently.

Abstract: A holder system for fastening an aircraft interior component to a transporting apparatus and to an aircraft structure includes an interior component holder configured to be connected to the interior component and which has a fastening device for fastening the interior component holder to the transporting apparatus. A structure holder is configured to be connected to the aircraft structure. A connecting element is fastened to the interior component holder and is configured to be connected to the structure holder in order to fasten the interior component to the aircraft structure.

Abstract: A holder for fastening an interior component, intended for mounting in an aircraft, to a transporting apparatus, includes an interface element configured to be connected to the transporting apparatus for the purpose of fastening the holder to the transporting apparatus. A bearing element is connected to the interface element and has a fixed bearing for bearing a first interior component holder connected to the interior component and a movable bearing for bearing a second interior component holder connected to the interior component.

Abstract: The present application describes a quick-change fastening system for demountably mounting an element to a fastening structure. The element comprises an engagement element that is designed to engage a bearing element of the fastening structure, wherein the element is hingeably held around the bearing element between a hooked-in position and a fastened position. The element further comprises a fastening element that can be affixed to a locking element of the fastening structure when the element is in its fastened position. The engagement element and the bearing element are designed such that along a hingeing movement of the element a form-fit connection is established when the element is in its hooked-in position, and that a force-fit connection is established when the element is in its fastened position.