Abstract: A method for manufacturing a load bearing structure involves providing a panel; providing a first set of split stiffening elements on a surface of the panel, wherein the split stiffening elements of the first set have bottom surfaces and central portions with open top clearances, respectively, spaced apart from each other; providing a second set of stiffening elements having bottom surfaces and top surfaces and central portions, respectively; inserting the stiffening elements of the second set into respective open top clearances of the split stiffening elements of the first set and providing the second set of stiffening elements on the surface of the panel for forming a grate structure; and attaching top surfaces to the split stiffening elements of the first set for forming complete profiles.

Abstract: A method for producing a tubular structural component and device for production thereof are disclosed. A tubular molding tool has an inner mold surface shaped corresponding to an outer surface of the structural component. A support surface of an expandable support, formed corresponding to the molding tool shape such that in an unexpanded state the support fills the molding tool while the support surface and the mold surface run parallel leaving an expansion spacing of the support surface to the mold surface, is covered with a tubular non-crimp fiber fabric, such that fibers of a fiber layer of the non-crimp fiber fabric run diagonally around the support. After the support has been arranged in the molding tool, the non-crimp fiber fabric is pressed against the mold surface by expanding the support with radial expansion of the non-crimp fiber fabric. The non-crimp fiber fabric is infiltrated by a curable matrix.

Abstract: An aircraft seat assembly for aircraft passengers having restricted mobility comprises a seat base assembly that comprises a first carrier device and a first fastening means. The aircraft seat assembly further comprises a wheelchair sub-frame, a second carrier device and a second fastening means. The dimensions of the wheelchair sub-frame are adapted to the dimensions of aisles provided in the aircraft cabin. Finally, the aircraft seat assembly comprises a seat which comprises a fastening means that is complementary to the first fastening means of the seat base assembly and to the second fastening means of the wheelchair sub-frame.

Abstract: A linking device including two hinge pins and having flexibility allowing vibrations between these two shafts to be filtered. The device includes a stack of plates connected to one another by layers of elastomer material. Plates of a first type are coupled to one of the shafts in relation to the movements parallel to the plates, while the plates of a second type are coupled to the other shaft in relation to the movements parallel to the plates, so as to allow relative movement of the shafts parallel to the plates. This linking device may be used in particular as a connecting rod, spreader beam or three-point shackle used in connecting a turbine engine to a pylon in a propulsion system of an aircraft such as an airplane.

Abstract: A standardized/modularized partition wall with a basic sandwich structure for purposes of separating a cabin area of an aeroplane. The partition wall has a multiplicity of defined zones for the flexible positioning of holding fixtures for the connection of accessories such as flat screens, baby carriers, newspaper racks, and similar, and which is dimensioned for a maximum population with accessories.

Abstract: The invention relates to a housing part containing a lubricant reservoir and at least one respective inlet and outlet opening for filling and draining a lubricating fluid into and from the lubricant reservoir. The inlet and outlet openings are sealed by releasable closure devices each comprising a sensor means for determining the operation parameters in a lubricant contained in the lubricant reservoir and for generating and/or storing sensor signals, as well as a transceiver for the transmission of the sensor signals to an external processing unit.

Abstract: A method and an apparatus for carrying out the method for installing an especially dome-shaped pressure bulkhead on a one-piece, substantially conical rear section for an aircraft, wherein said rear section includes a connection area and an end area. The method involves the steps of horizontally accommodating a prefabricated rear section in a horizontal support; inserting the rear section into a pivoting frame; pivoting the rear section into a vertical position using the pivoting frame, wherein the connection area of the rear section points upward; horizontally placing and centering the pressure bulkhead on the connection area, and joining the pressure bulkhead with the rear section in the area of the connection area.

Abstract: A supplementary power supply apparatus for electric onboard consumers of a vehicle, in particular flying machines. The apparatus includes openly disposed visible solar surfaces of several solar cells that are arranged in areas on the surface of an outer skin of the vehicle or integrated in the latter in the manner of a layer. Each of the solar cells includes at least two electric terminals by means of which the solar cells may be interconnected to form a solar generator, and several ones of the electric terminals are configured as generator terminals of the solar generator for one or several predetermined voltages between two respective ones of these generator terminals.

Abstract: A rail system for use when assembling a component in an aircraft comprises a first rail element having a securing device which is designed to be complementary to a first securing device provided in the region of a floor of an aircraft fuselage element and is adapted to cooperate with the first securing device in order to releasably secure the first rail element in the region of the floor of the aircraft fuselage element, wherein a section of the first rail element projects beyond an edge of the floor of the aircraft fuselage element in the connected state of the first rail element and the aircraft fuselage element.

Abstract: The invention provides a deployment mechanism 60 for deploying an auxiliary wing surface device 30 from an aircraft wing body 20, the deployment mechanism providing a first connector portion 75, 576 for connecting the deployment mechanism to the aircraft wing body, a second connector portion 65 for connecting the deployment mechanism to the auxiliary wing surface device, and a telescopic rod 61 linking the first and second connector portions, the telescopic rod comprising an inner rod 64 extendable from inside of an outer rod 63 to increase the length of the telescopic rod, such that the distance between the first and second connector portions can be increased. The invention also provides an aircraft wing 10, 510, an aircraft and a method of operating an aircraft.

Abstract: An aircraft windshield assembly includes at least one window pane, a frame against which the pane bears, at least one flange for clamping the pane against the frame, and at least one cavity delimited between the pane, the frame and the flange. A member of profiled cross-section substantially fills the cavity and over at least part of its periphery has formations in relief in the form of flutes which with a facing surface define seal-forming baffles.

Abstract: An assembly for an aircraft with an engine includes an attachment device intended to support the engine, a pod intended to surround the engine and including a cover, joints intended to allow articulation of the cover and allow movement of the cover relative to the attachment device between a closed position and an open position, and at least one access panel mounted moveably on the cover between a closed position, in which the access panel extends continuously between the cover and the attachment device when the cover is in the closed position, and an open position in which the access panel is remote from its closed position. The assembly includes a handle which can be operated from the outside of the cover between a first position and a second position, and a transmission system provided to move said or each access panel from its closed position to its open position.

Abstract: A device for machining a slot on a surface of a cellular structure includes a machining head that includes a chassis, a rotary tool rotating about a tool axis perpendicular to the direction of the slot, two guide wheels arranged on either side of the rotary tool that have a plurality of teeth configured and positioned such that they penetrate the cells of an alignment of the cellular structure. The machining head includes a link between the chassis and at least one guide wheel that enables a degree of freedom in a lateral direction parallel to the tool axis such that the guide wheel is movable in relation to the rotary tool in the lateral direction.

Abstract: An engine for propelling an aircraft includes an annular fuel cell arrangement having at least one fuel cell, at least one electric motor couplable to the fuel cell arrangement, at least one fan couplable to the electric motor and a cowling having an inlet and an outlet nozzle. The fuel cell arrangement is arranged inside the cowling, the at least one fan is arranged between the inlet and the fuel cell arrangement inside the cowling, the electric motor is operable under consumption of electric power delivered by the fuel cell arrangement and the at least one fan is designed to produce a thrust force by creating an accelerated airflow at the outlet nozzle. The engine is extremely efficient and comprises a distinct low noise.

Abstract: An aircraft comprising a mechanical connection device including a body that extends along a longitudinal axis. The body comprises two opposite end portions disposed along the longitudinal axis and adapted to receive external axial loads in compression and in tension, a spring member that is adapted to be compressed axially, and a mechanism which, in the event of external axial loads in compression or in tension on the end portions, is able to transmit to the spring member compression forces oriented in opposite directions according to whether the external axial loads are in compression or in tension. This device forms a flexible connection that accommodates equally well external loads in compression and in tension.

Abstract: A method of manufacturing a composite structural member (1), comprising the step of laying up a stack of fiber reinforced laminate plies (12), wherein at least one of the plies is laid up as discrete first (13) and second ply (14) portions, and the fibers of the second portion (14) have a different characteristic from those of the first portion (13). Also, a composite structural member (1) manufactured according to the method.

Abstract: A method for delivering announcements via a cabin communication facility comprising at least one cabin loudspeaker and via an on-board entertainment system comprising at least one headset output comprises the steps of delivering an announcement via the at least one cabin loudspeaker, beginning at a first instant, and delivering the announcement via the at least one headset output, beginning at a second instant, which differs from the first instant, the delivering of the announcement via the at least one cabin loudspeaker and the delivering of the announcement via the at least one headset output being initiated at differing instants.

Abstract: A cable raceway support device for an aircraft, formed from an electrically conductive material, comprising a pedestal having a fastening plane for the fastening of the device onto a primary structure and also having, on a support face which is an opposite face to the fastening plane, at least one pair of jaws having at least one electrical contact enabling a sliding electrical contact to be formed and the support face has a contact that projects, and also has a jaw overhanging the support face, the jaw forming with part of the pedestal the pair of jaws forming a stirrup-shaped clamp comprising a base and two branches, one branch of the clamp merging with the pedestal, and the other branch of the clamp corresponding to the jaw and bearing a second contact facing the first contact.

Abstract: An aircraft includes a system for influencing the yaw moment. The system includes a thrust generation means, an energy store which can be coupled to the thrust generation means for transmitting energy to the thrust generation means, and a trigger device. The thrust generation means is set up so as to provide a thrust force, including a thrust direction vector at a distance from a yaw axis of the aircraft. The trigger device is set up to couple the energy store to the thrust generation means at least for a predetermined period T on demand. The ability to compensate part of the thrust asymmetry independently of a rudder unit if an engine fails means that the rudder unit can be configured with smaller dimensions. This leads to a considerable reduction in the aerodynamic resistance of the aircraft, and thus to a weight-equivalent advantage, without leading to safety compromises.

Abstract: A curing tool for a shell component, includes a first tool component, which is cuboid and has a wedge-shaped bevel forming a first sheared edge on a first side edge, and a second tool component, which is cuboid, has a wedge-shaped bevel forming a second sheared edge on a first side edge and has a first corner bevel on a second side edge diagonally opposite the first side edge. The wedge angles of the first and the second sheared edge are equal.