Abstract: A receiving system for receiving of persons and objects for a cabin of a vehicle is proposed, the system comprising a seat frame having a plurality of receiving sections created on the seat frame for receiving of a seat unit each; a plurality of seat units, which are mountable on a receiving section each; and at least one stowage bin unit, which is mountable on one of the receiving sections. The stowage bin unit is dimensioned such that it is mountable on an outer one of the receiving sections in case on the remaining receiving sections a seat unit each is mounted.

Abstract: A mounting system includes a first and second mounting part having a first and second base part with a first and second plurality of first and second locking means respectively, for mounting two components to each other. Each of the locking means is attached to the respective base part and is provided with an attachment part extending from the base part, and a distal part provided as a head portion with at least one engaging section protruding sidewards over the attachment part. The locking means are laterally displaceable in relation to the base part to allow sidewards displacement of the engaging sections for engagement and disengagement of the locking means and thus the first and the second base. In the engaged state, latching means are provided blocking the sidewards displacement of the engaging sections to an extent that a disengagement of the locking means is prevented.

Abstract: A passenger seat device for a vehicle cabin comprises a front end and a rear end, a backrest arranged at the rear end, a plurality of seat surface segments extending from the rear end to the front end and a seat frame for carrying the seat surface segments and the backrest. The seat surface segments are arranged in a side-by-side relationship and constitute a seat surface and the seat surface segments are individually adjustable between at least two different vertical positions relative to the seat frame. The passenger seat device may flexibly seat passengers with different constitutions.

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: A high lift system for an aircraft, comprises a drive unit, a high lift surface, at least one primary drive station, each primary drive station having a shaft connection couplable with the drive unit and a primary lever couplable with the high lift surface. The high lift system further comprises at least one secondary unit, each secondary unit having a secondary lever couplable with the high lift surface. Each one of the at least one primary drive station is adapted for moving the respective primary lever on driving the shaft connection, and each one of the at least one secondary unit comprises a selectively activatable brake, such that the secondary lever follows the motion of the one of the at least one high lift surface when the brake is deactivated.

Abstract: A method is provided for coating a substrate, in particular a fiber reinforced plastic component, a protective layer being applied, with preference by means of thermal spraying, to a non-cured resin film applied to a release film, and subsequently, after removal of the release film, the resin film being applied to the substrate and cured.

Abstract: A device for the production of structural components from a fiber composite material, the components being three-dimensionally arched over a large surface, including a jig having a convex mounting surface having receiving channels for the insertion of structural components, wherein the loaded jig interacts with a laminating bonding device having a corresponding shape for forming the structural component under pressure, wherein the mounting surface includes a plurality of individually elastically deformable mounting shell parts arranged adjacent to each other along at least one longitudinally extending pitch line and attached to a plurality of elastically deformable supporting frame elements extending on the interior of the shell at a right angle to the pitch line, and a plurality of actuators for deforming the mounting surface between an extended position (A) and at least one retracted position (B) to move the jig from the bonding device relative to the receiving channels without undercuts.

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: An exterior structure component for an aircraft with an illuminating device includes a structure with an interior side and an exterior surface with at least one illuminated region and a multitude of optical fibers that extend from the interior side to the at least one illuminated region of the exterior surface. The optical fibers end on the interior side of the exterior structure component in a common interface area that is couplable to an illuminating device. The structure is made from a fiber composite material in which the optical fibers are integrated. In this manner a particularly weight-saving illuminating device that is capable of withstanding external influences may be provided.

Abstract: A system for interconnecting components in a vehicle body structure, and especially for interconnecting fiber-reinforced composite components in a fuselage structure of an aircraft. The system includes a first adapter member, a second adapter member and a connector member. The first adapter member has a first mating portion configured to substantially conform with a profile of a first component of the structure in more than one plane. A first attachment portion is connected to the first mating portion. The second adapter member has a second mating portion configured to substantially conform with a profile of a second component of the structure in more than one plane. A second attachment portion is connected to the second mating portion. The connector member securely interconnects the first and second attachment portions of the first and second adapter members. A related method of interconnecting components in a vehicle body structure is also disclosed.

Abstract: An electrical drive system for an aircraft includes: at least one first and one second electrical direct voltage sources for supplying a direct voltage, and a first and a second electrical machine modules configured to convert electrical alternating voltage into mechanical movement and vice versa. The first and second modules are connected to a first and a second power inverters, respectively. The first and second inverters are connected in series and the first and the second direct voltage sources are connected in series to generate an overall direct voltage to which the inverters are connected. The power inverters each has one voltage measuring device for measuring the power inverter direct voltage present at the respective inverter and a power inverter control device for controlling the operation of the inverters in accordance with the power inverter direct voltage.

Abstract: A method for manufacturing a lining panel with integrated electric lines for a lining of a passenger cabin of an aircraft or spacecraft includes using an additive manufacturing (AM) or 3D printing technique to form the electric lines on or into a panel body of the lining panel. A lining panel with integrated electric lines for a lining of a passenger cabin of an aircraft or spacecraft includes a panel body and electric lines being formed on or into the panel body using an AM or 3D printing technique.

Abstract: An aircraft wing comprising a main wing, a high lift element, and at least two spaced connecting systems for moveably connecting the high lift element to the main wing, wherein each connecting system comprises a track element provided on the main wing, and having a first support surface and a first track side wall, an actuator device, a drive rod, and a carriage device connected to the high lift element and having an engagement portion. The object is to provide an aircraft wing which is configured in such a manner that when the connecting system for connecting the high lift element to the main wing fails the high lift element can still be held in a possibly unskewed position.

Abstract: A device and to a method for the production of essentially two-dimensionally arched large-area structural components from a fiber composite material, including a jig having a convex mounting surface which has longitudinally extending receiving channels for the insertion of construction components and which can be loaded with auxiliary materials, wherein the loaded jig interacts with a laminating bonding device having a corresponding shape for forming the structural component under pressure, wherein the jig includes a mounting shell that at the edge can be elastically deformed inwards, which mounting shell, by way of a plurality of actuators that are articulated to the inside, can be moved between an extended position (A) and at least one retracted position (B) in which the jig can be moved relative to the longitudinally extending receiving channels from the laminating bonding device without undercuts.

Abstract: A flexible oxygen supply system which can easily be adapted to different seat layouts and which is significantly improved with regard to test and maintenance possibilities. An oxygen module includes an oxygen source, a mask and a tube between the oxygen source and a mask. The oxygen module further includes fastening elements for fastening in a supply duct of an aircraft, and a locking element by means of which the cover of the oxygen module can be locked.

Abstract: A cooling system cools at least one heat producing device provided in a unit of transport, and a method is provided for cooling at least one heat producing device provided in a unit of transport. The cooling system includes at least one first liquid circuit and at least one first heat exchanger assigned to the first liquid circuit, the first liquid circuit, for cooling the at least one first heat producing device, being configured to absorb heat of the first heat producing device via a cooling liquid circulating in the first liquid circuit and dissipate heat to the first heat exchanger, the first heat exchanger being coupled in such a manner to a first air-guiding system available on board the unit of transport, that exhaust air extracted from the first air-guiding system can be supplied to the first heat exchanger in order to recool the cooling liquid.

Abstract: A device for indicating an activation status of an aircraft emergency slide. The indicating device comprises an optical and/or acoustic signal emitting device, a status signal input, with a first input signal for an emergency slide activated state, and a second signal for a deactivated state, and a control, connected to the signal device, and to the status signal input, and configured to operate the signal device as a function of the status signal received, to indicate the status signal state. The indicating device comprises an inclination angle measurement device connected to the control for determining the inclination angle about a predetermined axis and provide an inclination angle signal output. The control determines, based on the determined inclination angle, whether a predetermined inclination angle has been exceeded for a predetermined time period and outputs, via the inclination angle signal output, a predetermined output signal only when this has occurred.

Abstract: A manufacturing method for passenger door corner components of aircraft or spacecraft includes using additive layer manufacturing, ALM, to form an integral passenger door corner component. The integral passenger door corner component includes a substantially cruciform shape having a frame coupling member with two frame couplings as end pieces. The frame coupling member intersect with a beam coupling member with two beam couplings as end pieces.

Abstract: A trolley for collecting waste products in a vehicle includes: a trolley housing with an upper housing opening to a housing interior of the trolley housing and a waste enclosure suspended in the housing interior and provided with an upper enclosure opening, and a fluid receiving container with an upper container opening and arranged in or laterally on the trolley housing. The enclosure opening and the housing opening are arranged relative to one another in such a way that waste products can be introduced through the housing opening and the enclosure opening. The fluid receiving container includes a container suction port, by which a fluidic connection can be produced to extract a fluid from the bottom of an interior of the fluid receiving container. A cabin monument with such a fluid receiving container, as well as to a system with the trolley and the cabin monument are also described.

Abstract: A door stop element for an aircraft door has a body which is formed at least approximately L-shaped, and which has at least one contact area on the outer side of one of the legs for fixed contact on the aircraft fuselage, and a stop surface on the inner side of the other leg for the aircraft door. The body has a cavity, on the inner side of which adjacent to the stop surface a rib is provided, which extends through the stop surface symmetrically on both sides of the longitudinal median plane that extends perpendicular to the stop surface.