Abstract: A compact galley segment, which allows to safely and temporarily fix trolleys outside of a closed storage space includes a first trolley storage space, a second trolley storage space, a retractable trolley restraint device and a plurality of vertically arranged walls. The first trolley storage space includes a plurality of delimiting walls defining an inner space for receiving at least one trolley and an opening for inserting or removing the at least one trolley into or from the inner space. The second trolley storage space includes at least one placement space for temporarily placing a trolley. The trolley restraint device is integrated into or onto at least one of the plurality of vertically arranged walls and is configured for releasably restraining a trolley temporarily positioned in the second trolley storage space and for being fully retractable into the outer contour of the galley segment.

Abstract: An aircraft panel with a laminate structure is provided that comprises a stack of a plurality of metal sheet layers, at least one fiber reinforced adhesive layer, and at least one cover segment. At least one outer layer of the metal sheet layers comprises at least two separate metal sheets that overlap with each other along their respective commonly adjoining edges, providing an overlapping joint of the two separate metal sheets. The at least one fiber reinforced adhesive layer comprises fiber elements embedded in a matrix structure. One of the at least one fiber reinforced adhesive layers is arranged between two adjacent metal sheet layers. Further, the at least one cover segment is arranged on an outside surface of the laminate structure, the cover segment covering a region of the overlapping joint. Still further, the at least one cover segment comprises at least one layer of reinforcement fibers.

Abstract: A solid overlay for laser shock peening is described herein. The solid overlay includes a transparent or translucent material, wherein the solid overlay is structured and adapted to a shape of a surface of a component to be treated by the laser shock peening. The solid overlay is configured to confine a plasma plume generated by laser light.

Abstract: A system is provided for producing components of composite material, and especially elongate or continuous components of fiber-reinforced polymer. The system comprises a winding mechanism for winding an elongate sheet of composite material about a winding axis that is at an angle to a perpendicular to a longitudinal axis of the elongate sheet so as to form a helical coil of wound sheet a mechanism is provided for drawing or conveying the helical coil of wound sheet along a process path, wherein the process path is preferably substantially parallel to the winding axis. A shaping mechanism forms or shapes the coil of wound sheet as it is drawn or conveyed along the process path. A corresponding method of producing a composite component is provided.

Abstract: A cooling system, in particular for use on board an aircraft, includes a cooling circuit allowing circulation of a two-phase refrigerant therethrough, an evaporator disposed in the cooling circuit, and a condenser disposed in the cooling circuit. A plurality of subcoolers is arranged in series in the cooling circuit downstream of the condenser.

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: A flow body and method for taking in and/or blowing out fluid through a plurality of openings in a flow surface section of a flow body is disclosed. In some aspects, the flow body includes a flow surface section that extends in a flow body wingspan direction and a flow body chord direction and with a plurality of fluid lines that lead into the flow surface section and respectively form an opening therein. In some aspects, the method includes taking in and/or blowing out fluid through at least one fluid line that leads into a flow surface section of a flow body and respectively forms an opening therein.

Abstract: Systems for storing an on-board-wheelchair on-board an aircraft are provided. In order to provide a stowage possibility for an on-board-wheelchair that requires less valuable space, an aircraft cabin is provided that comprises an on-board space unit and at least one stowage compartment for an on-board-wheelchair. The on-board space unit provides an on-board function, and is surrounded by a housing wall structure. The stowage compartment provides space to accommodate an on-board-wheelchair. The stowage compartment is at least partly surrounded by an enclosure structure. At least a part of the enclosure structure is provided by the housing wall structure.

Abstract: An aircraft flow body includes a flow surface exposed to an airstream during flight, at least one structural component attached to an interior of the flow surface, at least one perforated area having a plurality of openings extending through the flow surface, a manifold positioned interior to the flow surface in fluid communication with the openings and upstream of the at least one structural component, and at least one suction duct having a first end in communication with the manifold and a second end placed exterior to the flow surface downstream of the structural component. The at least one suction duct includes a suction opening facing away from the first end and adapted for inducing a suction force into the at least one suction duct when the flow surface is exposed to the airstream during flight, thereby inducing a flow of air from through the openings to the suction opening.

Abstract: An accumulator arrangement for use in a cooling system suitable for operation with two-phase refrigerant includes a condenser having a refrigerant inlet and a refrigerant outlet. The accumulator arrangement further includes an accumulator for receiving the two-phase refrigerant therein, the accumulator having a refrigerant inlet connected to the refrigerant outlet of the condenser and a refrigerant outlet. Finally, the accumulator arrangement includes a subcooler having a refrigerant inlet and a refrigerant outlet, the refrigerant inlet of the subcooler being connected to the refrigerant outlet of the accumulators, and the subcooler being arranged at least partially within the interior of the accumulator.

Abstract: A system for deploying loads out of an aircraft comprises an aerial delivery parachute with an aerial-delivery parachute line and an activation means for placing the aerial delivery parachute in an enveloping flow past the aircraft. Within the aircraft a receiving device can be positioned that receives a tractive force acting on the aerial-delivery parachute line, which tractive force has been determined by a force measuring device and has been transmitted by way of a transmitting device. With the knowledge of the tractive force it is possible both to implement emergency release and to assess whether an aerial delivery parachute has correctly deployed in the flow enveloping the aircraft.

Abstract: A monitoring device for monitoring a movement profile of a user in the region of an actuating element of an aircraft or spacecraft, having at least one movement sensor which is configured to detect a first monitoring space of the monitoring device and at the same time a second monitoring space of the monitoring device which differs from the first monitoring space. Also a method for monitoring a movement profile of a user in the region of an actuating element of an aircraft or spacecraft, with: detection of a first monitoring space of the monitoring device by at least one movement sensor; and simultaneous detection of a second monitoring space, which is different from the first monitoring space, by the at least one movement sensor.

Abstract: A riblet structure for a flow surface is provided. The riblet structure has a multitude of riblets that comprise a matrix material which includes reinforcement elements. The reinforcement elements can be designed as reinforcement fibers that extend in the longitudinal direction or as particles. In this manner the abrasion resistance can be improved and erosion can be retarded.

Abstract: A folding passenger seat and a corresponding passenger seating system for means of passenger transport are provided. The folding passenger seat comprises a seat frame, on which a front seat leg having a first fastening element and a rear seat leg having a second fastening element are arranged. The first fastening element and the second fastening element are configured to be connected to rails on a cabin floor of the means of passenger transport and to be displaced in the rails. A first joint element is arranged between the first fastening element and the second fastening element such that a spacing between the first fastening element and the second fastening element is variable. In particular, the first joint element may be arranged between the front seat leg and the seat frame or between the rear seat leg and the seat frame.

Abstract: An aircraft interior component system includes an aircraft interior component, a first structure holder fastened to an element of the aircraft structure, and a first component holder fastened to the aircraft interior component. The first component holder is fastened to the aircraft interior component in a first region thereof which faces an aircraft cabin ceiling when the aircraft interior component is mounted in an aircraft. The first structure holder and the first component holder attach the aircraft interior component in a suspended manner to the element, such that a mounting gap is present, at least in a second region of the aircraft interior component facing an aircraft cabin floor when the aircraft interior component is mounted in an aircraft, between a rear side of the aircraft interior component and an aircraft component opposite the rear side of the aircraft interior component.

Abstract: A device for installing a lining panel in an aircraft. The installation device comprises a main beam having first and second sections and a hinge pivotably connecting a first end of the first and second sections such that the first section can be pivoted relative to the second section about an axis perpendicular to a longitudinal axis of the first section. A first beam is provided at a second end of the first section, movable relative to the first section along its longitudinal axis, and a second beam is provided at a second end of the second section, movable relative to the second section along its longitudinal axis. Also, a first longitudinal element connected to an end of the first beam facing away from the first section, and a second longitudinal element connected to an end of the second beam facing away from the second section are provided.

Abstract: An evacuation slide comprises a sliding face having a top end portion adapted to be positioned adjacent to an exit of a region to be evacuated, and a bottom end portion adapted to be positioned adjacent to an escape route leading away from, and at a lower height, than the region. The sliding face, at the top end portion, comprises a flat porch section connected to an inclined section of the sliding face via a transition section. The sliding face has at least one of a first guidance marking placed in the flat porch section and having a shape and orientation adapted indicate a predefined evacuation direction in the inclined section of the sliding face and a second guidance marking placed in the transition section and having a shape and orientation adapted to indicate a separation between the flat porch section and the inclined section.

Abstract: A method for determining the position of a component in a high lift system of an aircraft, the high lift system comprising a central power control unit for providing rotational power by means of a transmission shaft; and actuator drive stations coupled with the power control unit and movable high lift surfaces. The method comprises the steps of acquiring a first rotational position of a first position pick-off unit mechanically coupled with the power control unit by means of a first gear having a first gear ratio, acquiring at least one second rotational position of at least one second position pick-off unit mechanically coupled with a driven element in at least one drive station, and determining the number of full rotations the first position pick-off unit has already accomplished between a neutral position and an intended maximum number of rotations.

Abstract: A method for coating a surface of an aircraft is provided. The method comprises the steps of cutting to size at least one film section from a shrinkable film material in such a manner that the film section relative to a surface section of the aircraft, which surface section is to be coated with the film section, comprises an overmeasure that is determined by the degree of shrinkage of the film material; applying the film section and a functional coating to the surface section so that the functional coating is arranged between the surface section and the film section; and shrinking the film section by heating it to a temperature that corresponds at least to the shrinkage temperature of the film section and at least to the flow temperature of the functional coating until the contours of the film section largely conform to the contours of the surface section.

Abstract: There is disclosed inter alia a transport goods monitoring device having a cover which is configured to cover transport goods received by a transport goods receptacle, the cover comprising a conductor arrangement, the conductor arrangement being in a first state when the cover is intact, the conductor arrangement being transformable from the first state into a second state by damage of the cover and the conductor arrangement being connectable to a detector which is configured to detect the existence of the second state. Furthermore, there is disclosed an arrangement comprising a transport goods receptacle which is configured to receive transport goods, and such a transport goods monitoring device, the cover of the transport goods monitoring device covering the transport goods receptacle and optionally transport goods arranged thereon. Also disclosed is the use of such a transport goods monitoring device for safeguarding transport goods received by a transport goods receptacle.