Abstract: An area projection system for reproducing a visual signal on a surface, comprising a light source, a fiber element comprising a plurality of light guide elements, a carrier element and imaging optics, wherein the fiber element comprises a first end and a second end, wherein the first end of the fiber element is arranged on the light source and the second end of the fiber element is arranged on the carrier element, wherein the imaging optics are arranged on the second end of the fiber element, wherein the area projection system is adapted to transmit a visual signal from the light source to the fiber element and subsequently to the imaging optics, and wherein the imaging optics are adapted to reproduce the visual signal on a surface.

Abstract: An aircraft structure is provided that includes, but is not limited to structural elements, a first multitude of lines that are in a fixed manner connected to structural elements, a second multitude of lines that are in a fixed manner connected to structural elements and whose longitudinal direction intersects the longitudinal direction of the first multitude of lines so that the longitudinal directions of the lines form a network that covers the aircraft structure at least in some sections, and connecting elements in order to, in the state of the structural elements installed in the aircraft structure, connect selected lines of the first multitude to selected lines of the second multitude of selected points of intersection of the network in order to in this way form transmission lines, such as lines for electricity transmission and/or data transmission. Furthermore, a method is provided for manufacturing such an aircraft structure.

Abstract: The present invention provides a structural element for an aircraft and spacecraft, having a core which includes core regions which are uncoupled from one another by means of an expansion joint arranged between the core regions. The present invention further provides a method for producing a structural element for an aircraft or spacecraft, including the following method steps: providing a core of the structural element, which core includes core regions; and arranging an expansion joint between the core regions. The present invention relates still further to an aircraft and/or spacecraft having such a structural element.

Abstract: A device for the temporary position fixing of adjacently arranged aircraft structures to be interconnected includes a support frame with at least one vacuum suction cup for temporary surface attachment and with clamping means for the position fixing of the aircraft structures to be interconnected. The support frame with the at least one vacuum suction cup in the region of a transverse gap is attached on the side of one aircraft structure. The support frame includes mechanical contact pressure means for the gap-bridging position fixing of the adjacent other aircraft structure. On the support frame there is a counter support to pressure elements of the contact pressure means.

Abstract: The invention relates to an arrangement for dividing a space into a plurality of areas, said arrangement comprising at least one frame with at least one fixing means for holding the frame in corresponding frame receiving elements, and at least one foldable defining means. The frame is formed in such a way that the arrangement essentially fits onto at least one wall of the space when it is fixed, the foldable defining means being able to be held on the frame and preventing an air flow between adjacent areas of the space separated by the arrangement. The arrangement according to the invention enables a thermal separation of two adjacent areas of a space, that can each be air-conditioned differently, without forming an area containing air which is a mixture from two regions at different temperatures.

Abstract: A transmission system for transmitting communications data from at least one data source to a plurality of terminals via a distributor, includes terminals connected in series in a terminal chain, via an input port and an output port. The first and last terminals in the chain are directly interconnected with a shunt connection in such a way that the communications data in the chain of terminals is transmitted from terminal to terminal, between the first and the last terminals of the chain if all the terminals are interconnected, and, if the connection between the terminals in the terminal chain is interrupted, the communications data from the first terminal of the chain of terminals is transmitted in the terminal chain up to the inactive terminal and the communications data from the last terminal is transmitted in the terminal chain up to the inactive terminal.

Abstract: A monitoring device and method are provided for monitoring a vacuum toilet, as well as a personal transport vehicle, in particular an aircraft, which uses a monitoring device for vacuum toilets. The monitoring device has a position detector for detecting the position of a toilet lid, a mechanical latching device and a flushing control unit. The latching device is designed to latch the toilet lid in an open position based on the weight of a person acting on a toilet seat. The flushing control unit is further designed to control the flushing operation based on the toilet lid position, and to block the flushing operation upon detection of the toilet lid in the open position. This makes it possible to improve both the comfort and hygienic conditions for the toilet user while using the vacuum toilet.

Abstract: A movable joining device for connecting structural components of an aircraft, with joining means moveably arranged on a guiding device situated on the outside of the structural components so as to fixedly connect joining edges of the structural components positioned adjacent to each other, wherein the joining means includes a welding unit that can move on the rail-like guiding device, and is equipped with a special so-called bobbin tool as a tool for friction stir welding.

Abstract: A modular cabin segment for a vehicle includes a first lateral segment module that accommodates a first toilet arrangement with at least one toilet compartment and a second lateral segment module, wherein in each case an outer lateral face of the first segment module and of the second lateral segment module is designed to adapt in each case to an inner wall of a cabin of the vehicle so as to correspond to the aforesaid. At least one of the modules includes at least one cabin attendant seat that on one side is held on the at least one module so that it can be pivoted on an axis. In this manner very good integration of many different functions in the manner of a construction kit is achieved in order to be able to accommodate a greater number of passenger seats elsewhere within the limited space provided in a cabin.

Abstract: An aircraft cooling system (10) comprises a cooling element (12), which comprises a housing (14), a cooling air inlet (18) formed in the housing (14) and a plurality of heat exchangers (32, 34, 36, 38), which are disposed on lateral surfaces (24, 26, 28, 30) of the housing (14) and through which cooling air supplied through the cooling air inlet (18) may flow. A cooling air supply channel (40, 40?) connects a cooling air supply opening (44, 44?) formed in a tail section of an aircraft to the cooling air inlet (18) of the cooling element (12). A cooling air outlet channel (46) connects the heat exchangers (32, 34, 36, 38) of the cooling element (12) to a cooling air discharge opening (50).

Abstract: A leakage detection device comprises a cuff of an elastic material for being circumferentially wrapped around a region of a fluid-carrying conduit, wherein the cuff has an inner surface and an outer surface, through which at least one opening extends. At least one holder that comprises at least one guide element for guiding a measuring element over the opening is arranged at the edge of the opening. In this way, the measuring element can be positioned at a predetermined radial distance from the opening.

Abstract: An aircraft outer skin heat exchanger includes a first cooling air inlet and a first cooling air duct section, in which a first heat carrier fluid duct section is arranged. A cooling air conveying device is configured to convey a cooling air stream in such a way through the first cooling air inlet and the first cooling air duct section that the cooling air stream is subdivided by a first heat carrier fluid duct section, arranged in the first cooling air duct section, into two partial air streams which flow through the first cooling air duct section substantially parallel to one another and in the same direction.

Abstract: The invention concerns a device for a adjustable flap adjustably mounted on a main wing surface of an aeroplane wing, in particular, a landing flap, with at least one adjustment unit for purposes of adjustment of the adjustable flap, which has an actuator arranged, or that can be arranged, on the main wing surface, and has a kinematic adjustment mechanism running between the actuator and the adjustable flap, wherein the adjustable flap is mechanically coupled with the actuator via the kinematic adjustment mechanism. At least one damping unit for purposes of damping a dynamic loading effected by the adjustable flap on the adjustment unit, which can occur as a result of a critical malfunction event occurring in the region of the adjustable flap, is arranged, or can be arranged, between the main wing surface and the adjustable flap.

Abstract: An installation system includes a structure for an aircraft, at least one carrier for an arrangement of at least one device of the aircraft, at least two attachment elements configured to attach the at least one carrier to the structure, and at least one mounting having an adjustable reception element receiving one of the at least two attachment elements.

Abstract: The invention relates to a rest compartment arrangement in an aircraft, comprising a rest compartment and at least one monument, wherein the rest compartment is arranged above a cabin floor and comprises a passage that extends from a rest compartment floor in the direction of the cabin floor. When compared to the state of the art, the invention is characterized in that the at least one monument comprises at least one wall which above a seat region situated therein forms a recess to accommodate the passage. As a result of this, monuments can be positioned in a space-saving manner underneath the passage in the cabin without this resulting in reduced comfort, because the recess above the seat region is not perceived to be distracting by the passenger.

Abstract: An interface element connects a first section of an aircraft supply system, which is provided on an aircraft interior equipment component, to a second section of the aircraft supply system and includes a carrier structure which is fastenable to the aircraft interior equipment component. Further, the interface element includes a connector element which is connectable to the first section of the aircraft supply system provided on the aircraft interior equipment component and which is mounted on the carrier structure by way of a bearing device. The bearing device includes at least one resilient bearing element which enables the connector element to be mounted such that it is movable in all three spatial directions.

Abstract: A device and a method for controlling the air humidity in a fuel cell detect a step response in the output voltage of a fuel cell when the supply to electrical loads is interrupted, and determine parameters of the dynamic time characteristic from the detected step response, and thus calculate a capacitance of the fuel cell. As a function of any deviation from a predetermined capacitance, a humidity control unit is caused to increase or decrease the humidity. This makes in situ detection of the humidity balance of a fuel cell possible, and this can keep the electrical power thereof constant for a relatively long period, and this can increase the intervals between maintenance.

Abstract: A mirror arrangement (10) for monitoring a passenger cabin of an aircraft is disclosed, comprising at least one mirror element (40) for reflecting light and a mirror mount (20) for fastening the at least one mirror element (40) inside the passenger cabin, the mirror mount (20) comprising a holder (22), to which the at least one mirror element (40) is fastenable and which is displaceable relative to the passenger cabin.

Abstract: A wing box for an aircraft wing with a framework and a first shell. The framework is connected to the first shell such that a load acting on the first shell can be transferred by the framework.

Abstract: A trailing-edge flap system is described. The trailing-edge flap system includes a trailing-edge flap and a movement device. The movement device includes at least a translatory mover for the translation of the trailing-edge flap and at least a rotational mover for the rotation of the trailing-edge flap.