Abstract: A device for delimiting a crew rest area in an aircraft passenger cabin includes a curtain which is adapted to separate at least one seat disposed in the aircraft passenger cabin from a region of the aircraft passenger cabin surrounding the seat. In addition, the device includes a fastening device for fastening the curtain in the aircraft passenger cabin. At least a first part of the fastening device is fixed to a grip rail intended for installation in the aircraft passenger cabin or formed integral with the grip rail intended for installation in the aircraft passenger cabin.

Abstract: A floor segment for a transportation system, in particular for an aircraft, for the spatial separation of an interior space of the into a lower space and into an upper space. The floor segment has an upper partition and a lower partition, which together with the upper partition encloses a hollow space, which is equipped for accommodating system component of the aircraft. Preferably, the floor segments are of a modular design so that within a floor individual floor segments can be exchanged for other floor segments that comprise identical or compatible dimensions and connections for the system components.

Abstract: A method for joining parts to be joined which are subject to tolerance in the aerospace sector. The method involves determining the geometric data of a first and second part to be joined, determining the joining gap dimensions of the first and second parts from the determined geometric data and arranging a plurality of shape elements which can be connected together in planar manner in a first region of a surface of the first part. The method moreover comprises application of a first adhesive layer onto the plurality of shape elements and in a second region of the surface of the first part. The method finally involves joining the first and second parts, the first adhesive layer being brought into contact with the surface of the second part. A corresponding apparatus is provided for joining parts which are subject to tolerance in the aerospace sector.

Abstract: According to the invention a main-load bearing skin shell for a structural component is provided, wherein the skin shell for being affixed to a support component comprises an outer edge section with an outer edge and comprises: a connection region that does not comprise a core layer, which connection region extends along the edge with the inner skin section and the outer skin section, wherein in an end region of the core layer along the outer edge section of the skin shell reinforcement devices are integrated that project through the shear-force-absorbing core layer.

Abstract: A structural component for an aircraft or spacecraft, comprising: a planar member; a reinforcing member which projects from the planar member and is rigidly connected thereto; the reinforcing member comprising at least a foam layer and a cover layer, a plurality of pins extending at least through the foam layer and the cover layer, and at least the pins and the cover layer comprising a curable matrix.

Abstract: The invention relates to a curtain support assembly to receive a curtain rail for a curtain for separating at least two regions in a cabin of a vehicle, comprising two or more header components for covering a space formed between the curtain rail and a ceiling in the cabin. The assembly according to the invention distinguishes itself from the state of the art in that between the header elements, for the purpose of holding objects, a hollow space is formed that is accessible by way of one or several closable openings to the cabin. In a further improvement, a roller is integrated in the hollow space, by way of which roller the curtain may be rolled up or down and may easily be stowed away.

Abstract: The present invention provides a method for the localized working of a structural component that comprises a foam material reinforced by at least one strut at a working location. Firstly, the foam material is selectively removed, while leaving the at least one strut, within a strut connecting zone in the region of the working location. Subsequently, the strut connecting zone is filled with a filling material and the at least one strut is connected to the filling material in the strut connecting zone. From a further aspect, a sandwich component which comprises a foam core is provided. An embedding part is at least partially embedded in the foam core and at least partially surrounded by a layer of filling material. At least one strut is incorporated in the foam material, fastened at one end to the surface of the foam core and integrated at another end in the layer of filling material.

Abstract: An aircraft having at least two separate aircraft fuselages is provided. The aircraft includes a first wing arrangement with at least two non-connected wing sections, and a second wing. In each case the wing sections of the first wing arrangement extend from the outside of an aircraft fuselage towards the outside. The second wing is arranged between insides of the at least two aircraft fuselages. Connecting regions of the first wing arrangement and of the second wing are arranged so as to be offset relative to each other at least on an X-Z-plane of an aircraft-fixed coordinate system. Consequently, the first wing arrangement and the second wing do not influence each other as a result of downwash, and in addition it is possible to do without horizontal stabilizer units that generate downthrust.

Abstract: A monitoring device is disclosed for an actuation system of an aircraft for monitoring a guiding device of a regulating flap with a load sensor. An actuation system with the monitoring device and a method for reconfiguring such an actuation system are disclosed. The monitoring device includes an interface to the load sensor and an interface to a driving device for adjusting the regulating flap. The monitoring device can determine or receive in-flight information actively signaling a predefined flight attitude and/or a predefined operational state of the aircraft. The monitoring device can compare a load value corresponding to a sensor value acquired by the load sensor and a limiting value corresponding to a minimum operational load for the predefined flight attitude and/or the predefined operational state of the aircraft and a monitoring function. The monitoring function can assign a fault mode to the regulating flap.

Abstract: The invention pertains to a fuselage segment (2) that extends in a longitudinal fuselage segment axis (A) and is closed in a circumferential direction (U) around this longitudinal fuselage segment axis, wherein the fuselage segment features: a plurality of shell components (4) for forming a skin of the fuselage segment (2) that respectively feature two first shell component edges (6) extending along a longitudinal shell component direction (LS) and two second shell component edges (10) extending along a lateral shell component direction (LB), wherein the shell components (4) are respectively connected to at least one adjacent shell component (4) along at least one first shell component edge (6) and along at least one second shell component edge (10), and wherein at least the direction of a tangent (T) on first shell component edges (6), on which two respective shell components (4) are connected to one another, and/or on second shell component edges (10), on which two respective shell components (4) are connec

Abstract: A flap arrangement includes a basic body, a hinge arrangement, and a flap that by the hinge arrangement is movably held on the basic body. The hinge arrangement includes at least three bearing points spaced apart from each other and arranged on a shared hinge line, wherein two bearing points are rigidly connected to the basic body and to the flap, and wherein the remaining bearing points in each case allow local movement between the basic body and the flap in at least one first spatial direction perpendicularly to the hinge line. Thus, load-induced constraint forces between the basic body and the control surface can be prevented.

Abstract: The present invention provides a method as well as a tool (1, 48) for producing a T-stringer, in particular in the aircraft and spacecraft sector. The method is characterized by two lay-up strips (3, 4) being arranged on top of one another, wherein areas (5, 6) of the lay-up strips (3, 4) corresponding to the stringer foot (60) that is to be formed, are spaced apart from one another by means of separation films (7, 8) and areas (14, 15) of the lay-up strips (5, 6) corresponding to a stringer web (61) come into direct contact with one another, in particular, forming a material bond. In a further method step, the lay-up strips (3, 4) are clamped at the areas (14, 15) corresponding to the stringer web (61) that is to be formed.

Abstract: A window replacement for filling a window frame in an aircraft is provided, in particular a passenger aircraft, the window replacement being fixable by a retainer in the window frame in place of the window assembly when the window assembly is removed. The window replacement comprises a panel-shaped element with at least a single curvature, the panel-shaped element being made of a synthetic material. The window replacement is formed by a monolithic panel-shaped element. The panel-shaped element of the window replacement may also be formed by a sandwich panel. This allows a weight reduction in comparison with a window replacement of a metallic material.

Abstract: A painting device for painting a curved surface (102) of an object (101), with a paint material ejection device (103), with a guide device (104, 105) and with a control device. The paint material ejection device (103) is designed for ejecting paint material. By means of the guide device (104, 105) the paint material ejection device (103) can be mechanically guided along a curved surface of an object. By means of the control device the paint material ejection device (103) and the guide device (104, 105) can be controlled in such a way that by means of guiding the paint material ejection device (103) along a predefinable path and by means of predefinable ejection of paint from the paint material ejection device (103) along the predefinable path a curved surface (102) of an object (101) to be painted can be painted.

Abstract: An indirect optical free-space communications system provides broadband transmission of high-speed data in transportation vehicles such as aircraft. The system includes a transmitter with a light source that can be modulated and a receiver with a photo detector, adapted to receive light that is emitted from the transmitter and to convert it into an electric signal. The transmitter and the receiver are directed onto at least one common surface, which reflects the light emitted from the transmitter before it reaches the receiver. The free space communications system is cellular and includes several cells, each of which has a transmitter and at least one corresponding receiver. The cells are configured in such a way that crosstalk with a respective adjoining cell is prevented. The cells are thus independent of one another.

Abstract: Disclosed is a seat bench transport device according to the invention for transporting a bench of seats for a vehicle, comprising a chassis, a retaining rail pair that is arranged on the chassis and includes two retaining rails extending parallel to one another for accommodating seat bench feet, the lengthwise sides of these rails that face one another being open at least in sections and the lengthwise sides thereof that face away from one another each having at least one locking section, and a displacement mechanism for moving the retaining rails transversely relative to one another.

Abstract: Fuel cell systems aboard means of transport can be used for generating energy and for producing water. In order to reduce the overall weight of the system, the fuel cell is controlled or regulated in dependence on a current fill level or a limit level of the water tank, as well as a predicted future water consumption. In this way, it may be possible to minimize the water quantity to be stored in the water tank.

Abstract: In a method for controlling an aircraft air conditioning system, a heating or cooling demand of an aircraft region to be air conditioned is determined. A volume flow of recirculation air discharged from the aircraft region to be air conditioned and a volume flow of compressed air into a mixing chamber of the aircraft air conditioning system is controlled such that the heating or cooling demand of the aircraft region to be air conditioned is met, while the volume flow of compressed air into the mixing chamber of the aircraft air conditioning system is minimized.

Abstract: A connecting device having two curved ribs of an aircraft or spacecraft, with: a coupling element which can be connected by means of predetermined coupling sections to respective connecting sections of the two ribs; wherein at least the predetermined coupling sections of the coupling element are rectilinearly designed; and wherein at least the respective connecting sections of the two ribs each have rectilinearly running inner belt regions for a respective rectilinear connection of the predetermined coupling sections of the coupling element.

Abstract: The present invention relates to an oscillator, particularly for or in a flat loudspeaker, particularly for use in the aerospace field, comprising an oscillating part carrier, a coupling ring for coupling the oscillator to a sound converter of a loudspeaker, wherein the oscillating part carrier and the coupling ring are connected to each other via a detachable quick-release closure, comprising first closing elements for a locked, secure connection in relation to vibrations and second closing elements that are separate from the first closing elements, for a secure connection between the oscillating part carrier and the coupling ring. The invention further relates to a flat loudspeaker comprising such an oscillator and to a vehicle comprising such a flat loudspeaker.