Abstract: A method of joining a first component to a second component, the method comprising preparing the first component by forming an array of elongate projections on a bond surface of the component, each projection having a centerline, a tip, and a base. The centerline at the tip of each projection is oriented at an angle with respect to the normal to the bond surface at its base, and the angular orientation of the tip centerlines varies across the array of projections. Next, the first component and a flexible layer are brought together so as to embed the projections in the flexible layer before hardening the flexible layer to form the second component. Also, a joint so formed.

Abstract: An aircraft fuselage includes at least one opening that can be closed by a flap or door, which comes to abut against at least one door stopper that is arranged on a fuselage-side door frame bulkhead and transfers the impact forces into an intermediate costal for diversion into an aircraft structure that encompasses bulkheads, wherein the door frame bulkhead exhibits an opening, through which an impact section of the door stopper extends, wherein a fastening plate section adjoining the latter comes to abut the rear side of the door frame bulkhead, which interacts with means for directly introducing the impact forces from the door stopper into the intermediate costal.

Abstract: A fuel system includes a fuel tank, a vent tank fluidically connected to the fuel tank ullage, the vent tank having a duct open to the ambient atmosphere and the interior of the vent tank, and a catalyst disposed in the duct, wherein the catalyst is adapted to deplete one or more reactive components of gas flowing through the duct by catalytic reaction. Also, a method for depleting one or more reactive components of gas in the fuel system, includes depleting one or more reactive components of gas flowing through the duct using the catalyst.

Abstract: A cabin attendant seat (14) comprises a backrest element (20) and a seat element (22) which is secured to the backrest element (20). The backrest element (20) is rotatable about a rotation axis (24a, 24b) in order to move the cabin attendant seat (14) between a rest position and an operating position. A fastening device (18) for fastening the cabin attendant seat (14) to a side wall (16) of an aircraft monument (12) is constructed and sized in such a manner that it is capable of directing away a predetermined maximum force which can be introduced into the cabin attendant seat (14) during operation of the cabin attendant seat (14) via the side wall (16) of the aircraft monument (12).

Abstract: A molding tool for manufacturing a fiber-reinforced plastic aerodynamic aircraft component, which aircraft component, in order to form several bays arranged on the inside and delimited by an outer skin and spars arranged spaced apart from each other, in each case includes a multi-part mold core that matches the shape of the respective bay, wherein to conform to local skin reinforcements and/or spar reinforcements that extend into at least one of the bays, the multi-part mold core includes four or five core parts, of which two core parts comprising a triangular cross section are arranged along opposing edges of the bay, which edges interact with two or three core parts that fill the space between the two triangular core parts, which space extends diagonally relative to the bay.

Abstract: The support (1) comprises a main body (3) which has a convex shape comprising facets which are planar and curved and free of edges, and it is provided with main contact surfaces (5) each of which is able to accept an electric cable, and with openings (6) surrounding each of the main contact surfaces (5).

Abstract: A high lift system for an aircraft with at least one high lift flap arranged on each of the main wings of the aircraft. The high lift system includes an input device for the generation of flight phase-related requirements for the high lift flap. The high lift system further includes a control device, with a conversion function with which the flight phase-related requirements are converted into setting commands for the actuation of a lift device for the adjustment of the high lift flap. The conversion function is configured such that from a take-off requirement, a setting command to the drive device is generated with which the leading edge flap of the high lift flap is arranged in a set state in which a gap exists between the leading edge flap and the main wing with a gap width of between 0.1% and 0.4% relative to the local wing chord.

Abstract: The invention relates to a wing with an extension in the wingspan direction, in the wing chord direction and in the wing thickness direction for use in an aircraft, with a retractable wing end piece. A mechanical lever system is here used, which can execute a pivoting motion of a wing end piece comprising both a rotational component and a translational component. The lever kinematics here comprises two lever arrangements, for which a respective two hinged devices are provided.

Abstract: A method for obtaining a composite material part from a preform of layers of fibers pre-impregnated with resin stacked on top of one another on a tool, the preform being delimited by a lower surface, an upper surface, and a peripheral flank. The method includes attaching to the tool, after the last layer has been laid, a peripheral part comprising a wing adapted to cover the peripheral edge of the upper surface, so as to create, in the periphery of the preform, a peripheral cavity adjacent to the flank of the preform and, before the polymerization phase, to withdraw the gas present in the peripheral cavity so as to tension filaments of the preform by exerting a traction force at the ends of the filaments.

Abstract: A hinge assembly for rotatably mounting a control surface on an aircraft comprising an actuating shaft, a support element configured to mount the actuating shaft to a first component of an aircraft and a hinge element configured to mount the actuating shaft to a second component of an aircraft, wherein the actuating shaft is slidably mounted to the support element and configured to slide along its longitudinal axis relative to the support element, and the hinge element engages with the actuating shaft so that the actuating shaft and the hinge element are urged to rotate relative to each other about the longitudinal axis of the actuating shaft when the actuating shaft is urged to slide along its longitudinal axis, such that one of said first and second components is urged to rotate relative to the other said component about the longitudinal axis.

Abstract: A fastener assembly is disclosed for mounting a component to a bracket attached to an inner surface of the skin of an aircraft wing such that the component is thermally and electrically isolated from the bracket is disclosed. The component and bracket each have mounting holes and the fastener assembly includes a fastening element having a shaft to extend through the holes, first and second isolating members mountable on the shaft on either side of the bracket such that the bracket is sandwiched between the first and second isolating members.

Abstract: A hand-drying device for an aircraft can be integrated into a washing stand, so that the hand washing and hand drying process can be performed within the washbasin of the washing stand. Corresponding sensors make this process contactless.

Abstract: A method is disclosed for automatic monitoring of a flight management assembly of an aircraft implementing air operations necessitating guaranteed navigation and guidance performance, wherein flight path data generated by first and second flight management systems respectively, are compared in order to check their consistency; first and second flight management systems transmit their flight path data to a third flight management system; the third flight management system receives a current position of the aircraft, calculates deviations between this current position and a flight path depending on the flight path data received from the first and second flight management systems, which it utilizes only if they are identical, and calculates, according to these deviations, guidance commands for slaving onto this flight path. Monitoring can compare deviations and guidance commands received from the first second and third flight management systems in order to be able to detect an inconsistency between them.

Abstract: An aircraft nacelle with a connecting device between a first conduit of an air intake and a second conduit of a motor, both conduits being arranged end-to-end, the connecting device including an annular flange connected to the air intake, an annular flange connected to the motor pressed against annular flange of the air intake, the flanges extending in a plane perpendicular to the longitudinal axis of the nacelle; bolt holes formed in annular flanges and disposed plumb to one another; and connecting elements located in bolt holes, for connecting the annular flanges, wherein at least one flange includes at least one opening interposed between a bolt hole and junction zone of the flange and/or between a bolt hole and outer edge of the flange.

Abstract: A smoke detection system includes at least one smoke detector which is installed in a first partial region of a region to be monitored by way of the smoke detection system. The smoke detection system further includes at least one fluid injection device which is configured to inject a fluid into the region to be monitored by way of the smoke detection system in a direction of at least one smoke detector such that in an emergency case, when smoke is present in a second partial region of the region to be monitored the smoke is transported to the at least one smoke detector.

Abstract: A calibration block and method for sensitivity calibration. The calibration block has a curved calibration surface having a central axis and a surface for coupling to a transducer element of an angular scanning phased array ultrasonic testing scanner. The block is configured such that the surface positions the transducer such that its scanning axis is coaxial with the central axis of the curved calibration surface.

Abstract: Toilets of a toilet system on board a vehicle are supplied with flushing agent from decentralized supply devices. Disposal of the wastewater takes place by way of a central disposal device. Thus, a toilet system without central supply of the toilets with flushing agent is stated, as a result of which weight may be saved.

Abstract: A lightweight structure at least sectionally composed of a plurality of connected mosaic elements and/or skin mosaic elements. The lightweight structure allows an essentially load-appropriate arrangement of the mosaic elements and/or the skin mosaic elements including the optional skin. The lightweight structure requires a significantly reduced number of connecting elements, such that the assembly effort can be reduced and an additional weight reduction can be achieved. Also, two variations of a method for manufacturing a lightweight structure are provided. Large-format lightweight structures such as, for example, an aircraft fuselage cell or partial shells thereof can also be manufactured in a reliable and dimensionally accurate fashion because only mosaic elements and skin mosaic elements, with relatively small dimensions, need to be handled.

Abstract: A method and device for automatically determining an optimized approach and/or descent profile for an aircraft are provided. The device comprises means for optimizing an approach and/or descent profile of an aircraft avoiding long and steep geometric segments, the device to this end inserting an idle segment, if it satisfies the restrictions, in the profile relating to the descent phase and/or to the approach phase, wherein said idle segment can be followed by a geometric segment.

Abstract: A fastening arrangement for attaching a floor to a support structure is provided. The arrangement includes across beam, a floor panel deposited on the cross beam, a fork bolt attached to the cross beam via a barrel nut, and a lug bolt rotary connected to the fork bolt for attaching an attachment element to the cross beam. The fork bolt has a head for accommodating an end of the lug bolt. The fork bolt has a foot with a thread to be screwed into a thread of the barrel nut. The floor panel has an opening for accommodating the head of the fork bolt, such that the floor panel is attached to the cross beam by the fork bolt. The head of the fork bolt is rotatable in the opening of the floor panel for screwing the fork bolt into the barrel nut by rotating the lug bolt.