Abstract: A shrouded pipe formed from inner and outer pipe sections, the inner pipe section having an outwardly projecting flange joining the outer pipe section, and the outer pipe section having an inwardly projecting flange joining the inner pipe section, an annular volume between the inner and outer pipe sections providing a secondary fluid path. The flanges control axial position of the inner pipe section. By providing one flange which extends radially outwardly and one which extends radially inwardly, assembly is possible of the shrouded pipe by inserting the inner pipe section into the outer pipe section, without modification of the outer pipe section or inner pipe section. The first and second flanges ensure no unwanted contact between the inner and outer pipe sections and, therefore, prevent damage to the primary fluid path. The first and second flanges ensure good load distribution between the inner and outer pipe sections.

Abstract: A system for detecting overpressure in an aircraft including a door with a door frame and a door leaf with a first and second door leaf face. The door is mountable in an aircraft where the first door leaf face faces the interior and the second door leaf face faces the surroundings of the aircraft. The door leaf is movably attached to the door frame and selectively movable between an opened position where a door opening defined by the door frame is accessible and a closed position where the door leaf closes off the door opening. The door has a pair of contact faces including a first contact face on the door leaf and a second contact face on the door frame.

Abstract: A fastening system for fastening a first component variably spaced on a second component has a main body, a slide, and an elongate locking element. The main body has a mounting surface for mounting on the first component and a locating surface, through which an elongate depression passes, for fastening to the second component. The main body has a slideway to movably support the slide along the depression and the locating surface. Facing sides of the slide and the depression each have a first tooth system. The locking element fits into the elongate depression and has a second tooth system on two mutually opposite longitudinal sides and engages between the depression first tooth system and the locking element and between the slide and the locking element in a first alignment within the depression and releases it in a second alignment. The mounting surface and locating surfaces are not parallel.

Abstract: A system has a frame with first and second spaced apart edges, a first holder couplable to the fuselage structure and embodied for articulated connection to a first region of the frame that is close to the first edge, a second holder couplable to the fuselage structure, and a strut. A first end of the strut is connectable in an articulated manner to the second holder. A second end of the strut is connectable in an articulated manner to a second region of the frame near the second edge and remote from the first edge. The frame and the strut form a triangular structure with the first and second holders. The strut and the frame form two sides of the triangular structure. A length of the first and/or second side is variable to adjust the position of the frame.

Abstract: A coupling member for coupling modules with each other. The coupling member comprises a coupling portion, which in turn has a coupling rim and at least two hook members disposed on the coupling rim. The coupling portion substantially corresponds in its outer contour to a spherical segment of a sphere with a predetermined spherical radius, wherein the coupling rim represents a circular disk of the spherical segment. In this case, an outer radius of the coupling rim is smaller than or equal to the spherical radius. The at least two hook members, in a lateral view, at least partially follow the outer contour of the spherical cap of the spherical segment. The at least two hook members are engageable with the hook members of a coupling portion of a second coupling member.

Abstract: A composite structural element comprising a substantially planar main section defining a coordinate system with a first axis extending along a longitudinal axis of the structural element and a second axis extending perpendicular to the longitudinal axis within the planar main section. The structural element contains a basic lay-up of single plies, each comprising a fiber-reinforced composite material with a substantially unidirectional fiber orientation. The lay-up comprises N plies arranged from top to bottom in the following form: [[?, ?]M; [?]K; [?, ?]M], wherein ?, ? and ? represent one ply having an angle enclosed between the first axis and the unidirectional fiber orientation of the one ply, respectively, [x]y means y plies each having angle x; [x, y]z means z pairs of plies, K and M are both positive integers equal to or greater than 1: N=4·M+K.

Abstract: A supervision system for an aircraft for monitoring a safe charging of portable electrical devices of a passenger who may be in an attentive or an inattentive state, comprising a passenger seat, a power supply station assigned to the seat and used to supply electrical power to the portable electrical device, the portable electrical device being connected to the power supply station, a camera, which detects the state of the passenger situated on the seat, and an arrangement to distinguish whether the passenger is in an attentive or inattentive state. A method for safe charging of portable electrical devices is also presented and described, comprising the steps of detecting a passenger with a camera, analyzing whether the passenger is in an attentive state or in an inattentive state, and, if the passenger is in an attentive state, supplying a power supply station with electrical power to be provided to a portable electrical device connected to the power supply station.

Abstract: A passenger door arrangement for an aircraft segment, which arrangement comprises a passenger door, which is configured to assume a raised state and a lowered state, and a “girt bar,” for arming and disarming an escape slide, the girt bar not altering its position relative to the passenger door in the transition from disarming to arming, when the passenger door is in the lowered state. Additionally an aircraft segment, which comprises the passenger door portion and a fuselage portion, an external engagement arrangement being fixed to the fuselage portion.

Abstract: A wing for an aircraft, including a main wing, a slat, and a connection assembly movably connecting the slat to the main wing, such that the slat is movable between a retracted position and at least one extended position. The connection assembly includes a first connection station and a second connection station spaced apart from the first connection station in a wing span direction. The object, to prevent the slat from skewing, is achieved in that the connection assembly includes a sync shaft coupling the first connection station to the second connection station for sync movement of the first and second connection stations.

Abstract: A 3D printing device includes a printing substrate, a movable printing head configured for additively producing from a modelling material a component on the printing substrate, and a flexible printing space cover which, proceeding from the printing head, spans the printing substrate such that a closed printing space is formed between the printing head and the printing substrate, wherein a printing nozzle of the printing head for applying the modelling material protrudes into the printing space. A support structure of the device includes flexible support rods which run from the printing head to the printing substrate and which hold the printing space cover above the printing substrate.

Abstract: The disclosure refers to an airplane's own mobility system. For supporting a passenger with reduced mobility on board an airplane and for simplifying as much as possible the use of a toilette, a mobility system for passengers with reduced mobility is provided. The mobility system includes an onboard toilette spatial unit having an entrance zone, an entrance door, and a toilette using zone with a toilette. Moreover, a movement device with a passenger carrying equipment is provided, which is moveable at least from the entrance zone to the toilette using zone and supported in the ceiling area. The passenger carrying equipment includes a seat device enabling a passenger a seat like position. For using the toilette, a passenger is movable back and forth with the movement device from the entrance zone to the toilette using zone.

Abstract: A linkage mechanism for a flaperon includes a support structure linkage, a droop panel linkage, and a flaperon linkage. The support structure linkage is pivotally attached to a support structure of a wing of an aircraft. The droop panel linkage is pivotally attached a droop panel. The flaperon linkage is pivotally attached to a flaperon. A second end of the droop panel linkage and a second end of the flaperon linkage are pivotally attached to a connecting section of the support structure linkage. The connecting section is spaced apart from the pivot end of the support structure linkage such that the linkage mechanism transfers a pivoting motion from the flaperon into a pivoting motion of the droop panel.

Abstract: A cargo hold component system for a cargo hold of an aircraft, the cargo hold component system including floor elements and fixing elements. The floor elements can at least partially be fixed releasably by the fixing elements to fixing sites provided on or in the hold floor, such that in a state fixed to the fixing sites, the floor elements support a loading of the hold with cargo containers, and that in a state in which a first group of the floor elements has been removed from the fixing sites by release of the fixing elements and a second group of the floor elements has been partially removed from the fixing sites by release of the fixing elements, the hold is sealed gas-tightly.

Abstract: An electrically heatable layer stack is disclosed. The electrically heatable layer stack includes at least two substrate layers, and at least one carbon nanotubes-, CNT-, layer, which is arranged between the substrate layers and which is configured to conduct an electric current. The substrate layers and the at least one CNT-layer are configured to produce heating of at least one of the substrate layers when an electric current is applied to the at least one CNT-layer. A vehicle assembly group, an aircraft, a method and a system for manufacturing an electrically heatable layer stack are also disclosed.

Abstract: A temperature regulating system for at least one galley compartment for an in-flight kitchen which is intended for installing in a transport apparatus or vehicle, especially in an aircraft, includes a controllable cooling and heating element, which is designed for selectively cooling or heating a specified section of the cooling and heating element, and a heat-insulating partitioning wall, which at least partially adjoins an encompassing side edge of the cooling and heating element and encloses the specified section of the cooling and heating element. The heat-insulating partitioning wall is designed for separating an interior space of the galley compartment from an interior of a section of a fluid duct which extends in the in-flight kitchen.

Abstract: A system for representing a vehicle cabin layout on an original scale comprising a plurality of projectors, a planar projection surface and a control system. The layout is loaded as digital cabin layout data into the control system and the layout comprises a first cabin aisle section extending along a first aisle axis. The projectors comprise vertical projectors spaced along a first projector axis. The control system drives the vertical projectors and processes cabin layout data loaded into the control system to project at least one section of the cabin layout on the planar projection surface on the original scale. That section of the layout which is projected by the vertical projectors comprises the first aisle section, such that the first aisle axis runs with the first projector axis in a first aisle plane extending perpendicular to the planar projection surface.

Abstract: A wing (5) for an aircraft (1) and include a fixed wing (7), a high lift system (9) including a high lift surface (27) movably mounted to the fixed wing (7), and a high lift actuation system (29) for moving the high lift surface (27) relative to the fixed wing (7) between a retracted position and at least one deployed position, a foldable wing tip portion (11) mounted to the fixed wing (7) pivotally about an axis of rotation (35) between an extended position and a folded position, a tip actuation unit (13) for moving the foldable wing tip portion (11) between the extended position and the folded position.

Abstract: A cabin monument arrangement for a passenger cabin of an aircraft, has at least two cabin monuments arranged next to each other, aligned substantially parallel and forming a gap. The gap includes a gap covering in the fastening region of the first lateral monument part and of the second lateral monument part in the region of the front edge portion of the respective cabin monument. In each case, a first contour-adapted rigid fastening strip is on the fastening region and a second contour-adapted, rigid fastening strip is on the second fastening region. A covering element is between the first and second fastening strips for covering the gap between the first monument part and the second monument part, the covering element formed from a flexible covering material of thin design. A corresponding covering of the gap between the cabin monuments can therefore be achieved with sufficient flexibility and material width.

Abstract: A system and method for minimizing buffeting in the case of an aircraft. Buffeting load control elements are provided in airfoils of the aircraft are arranged to be at least partly moved out of the airfoils by a control to reduce buffeting loads acting on the aircraft.

Abstract: A panel structure for a vehicle, and especially for an aircraft or spacecraft, includes an area member, especially a skin member, that defines an areal expanse with a first surface and an opposite second surface and having a thickness between the first and second surfaces; and a plurality of elongate stiffener members which are attached to the area member and extend over at least one of the first and second surfaces; wherein at least one of the stiffener members is bifurcated at a bifurcation point into two or more branch stiffener members.