Abstract: A sealant smoothing tool for smoothing sealant in a gap between two aircraft parts is disclosed including a main body having a base surface for abutting sliding along a top surface of the aircraft parts, a spatula holder for holding a spatula, the spatula holder being configured to movably mount the spatula relative to the main body, and a resilient biasing member, configured to provide a biasing against the spatula or the spatula holder, such that the spatula supplies a biasing force to the sealant. An aircraft having two parts sealed by the sealant smoothing tool, a kit of parts including a sealant smoothing tool and one or more spatulas, and a method of smoothing sealant to seal a gap between two aircraft parts are also disclosed.

Abstract: A actuator arrangement is disclosed in which the high-lift device support that supports and guides movement of a high-lift device, such as a flap, is in axial alignment with a control actuator assembly that controls one or more control surfaces. This allows a single support fairing to be sufficient for covering both the track member and the control actuator assembly and allowing for reduced drag and weight.

Abstract: A fastening system for an aircraft to fasten at least one tank to contain liquid hydrogen, allowing easy access to the tank. The fastening system includes a longitudinal box, upper formers fastened to the upper end of the longitudinal box and lower formers fastened to the lower end of the longitudinal box, at least two upper formers including two fastening devices to each connect a fastening point of the tank to an upper former, at least one lower former including two second fastening devices to each connect a second fastening point of the tank to the lower former. The fastening system allows an operator to access the tanks that are capable of being fastened by the fastening system.

Abstract: An aircraft wing, including a main wing and a trailing edge high lift assembly movably arranged at a main wing trailing edge, the high lift assembly including a flap and a connection assembly movably mounting the flap to the main wing, such that the flap is movable between retracted and extended positions. In the extended position, a gap is present between a main wing lower rear panel and a flap leading-edge section. In the retracted position, the gap is closed or minimized. The flap is movable between an extended position, a first retracted position, and a second retracted position where the flap is moved beyond the first retracted position in a forward direction, and the wing comprises a gap closing device configured to close or minimize the gap in both the first and second retracted positions of the flap, and to open the gap in the flap extended position.

Abstract: A component includes at least a first sub-component and a second sub-component each fully or partially including metal or metal alloy material or having an at least partially metallized surface or surface region, the first sub-component and the second sub-component providing a pair of connection interfaces configured to establish a permanent connection of the first sub-component and the second sub-component, wherein at least one of the pair of connection interfaces comprises nanowires. The disclosure further provides a method for manufacturing such a component.

Abstract: A method for operating a water supply system for an aircraft, as well as a corresponding water supply system operating in accordance with the method and an aircraft having such water supply system. The method includes two operation sequences of a pump and a valve, each sequence including a time delay between operation of the pump and operation of the valve.

Abstract: A device for latching a door of an oxygen mask container in an aircraft cabin includes a door for an oxygen mask container having an inner side, outer side and hinge, a first latching device attached to the inner side, and a second latching device movable relative to the first latching device to selectively engage or disengage the second latching device. A retaining element is attachable to a structural part inside the oxygen mask container. A test control device on the inner side of the door includes a movable hook element and can move the hook element to a first or second position. The hook element can engage the retaining element in the first position to restrict an opening degree of the door. The hook element is placed in the second position such that when the door is opened, the hook element is moved past the retaining element.

Abstract: A method for assembling aircraft panels by welding improves the flexibility thereof. Panels are butted together along longitudinal joining lines and fixed to one another via their longitudinal edges by welding without the longitudinal ends of their welded edges being connected to one another. Longitudinal hoops are fixed to partially cover the concave surface of the panels at least partially at the ends. The absence of welding at the ends introduces the desired flexibility. The disclosure also covers the fuselage portions formed by assembling panels according to this method and the aircraft including such portions.

Abstract: To achieve a composite material part with a fully load adapted 3D fiber reinforcement with low costs for tools and process, a method is provided for manufacturing a part made of composite material with a continuous fiber reinforcement. The method comprises the steps of providing a body with tubular cavities and having at least one first portion made from a first polymer material and at least one second portion made from a second polymer material, introducing resin and continuous fibers into the tubular cavities, and removing at least a part of the second polymer material.

Abstract: A structural part for lightning strike protection, preferably of an aircraft includes a first structure element, wherein the first structure element includes a conducting material and is adapted to conduct electric currents into a grounded conducting airframe structure, and a second structure element, wherein the second structure element includes an outer layer with a first surface, wherein the outer layer includes a composite, preferably carbon-fibre reinforced plastic, CFRP or glass-fibre reinforced plastic GFRP. The structural part further includes a first elongated, preferably wedge-shaped, electrical conductor, with a first end and a second end, wherein the first end of the first elongated electrical conductor is connected to the first structure element and extends through the second structure element to the first surface, so that the second end of the first elongated electrical conductor serves as a lightning receptor without impairing the radar cross section of the aircraft.

Abstract: A spark containment cap for enclosing an end of a fastener protruding from a structure, the enclosed body having a base and a cover portion, the cover portion extending from the base, the base providing an adhering surface for adhering the spark containment cap to a structure, and the base and the cover portion together forming a cavity within the enclosed body inside which the end of a fastener can be enclosed.

Abstract: An unmanned ground-based transport vehicle, UGV, includes a housing, having a base plate and at least one housing side wall substantially perpendicular to the base plate. Arranged in the housing is at least one wheel drive, which is coupled to at least one wheel. The wheel is arranged in a recess in the base plate. The UGV further includes sensors for sensing the environment of the UGV, and a controller for autonomous location and navigation of the UGV on the basis of sensing parameters of the sensors. The UGV includes at least one load-receiving element coupled to the housing side wall and extending outwards from the housing side wall, wherein the load-receiving element includes a load support surface for supporting an item with respect to a vertical direction which extends transverse to the base plate.

Abstract: A support for the maintenance of an aircraft radome comprising an annular element having a flat surface and from which extend at least three feet. The support comprising a plurality of articulated holding elements, for example articulated fittings, applying a lock function and each comprising a bearing surface on a surface portion of an aircraft radome, for example an interface fitting, when said radome is placed on said flat surface of said annular element.

Abstract: A method for manufacturing at least a portion of a box structure obtained from an outer skin and a plurality of sections each having a joining face in contact with the outer skin. The method comprises a step of positioning the sections on a mold, a step of obtaining a flat fiber preform having a thickness substantially equal to the outer skin, a step of placing a central portion of the fiber preform on the sections positioned on a first face of the mold and a step of forming a lateral extension of the fiber preform to press the fiber preform against a forming surface. A central wingbox obtained by the method is provided and a forming tool for carrying out the method.

Abstract: A connector for a structurally integrated line system of a vehicle, having a first end portion, a second end portion and a connecting piece extending between the first end portion and the second end portion, wherein the first end portion has at least one contact face for arrangement on a structurally integrated line, wherein at least one of the at least one contact face has a cutout which is surrounded by a closed border, wherein the second end portion has a flange connection for connection to a pipe.

Abstract: A wing for an aircraft includes a leading edge as a first chordwise edge, a trailing edge as a second chordwise edge, an upper skin extending between the leading edge and the trailing edge, a lower skin extending between the leading edge and the trailing edge, at least one spar extending between the upper skin and the lower skin in a spanwise direction to create wing box with the upper skin and the lower skin, and at least one of a fluid line, an electrical line, and a mechanical power transfer device attached inside or reaching into the wing box at least partially.

Abstract: An acoustic treatment panel includes at least one acoustically resistive layer, a reflective layer and at least one cellular structure interposed between the acoustically resistive layer and the reflective layer. The cellular structure includes cylindrical and identical main tubes which are closed at one end by the acoustically resistive layer and at the other end by the reflective layer, spacer zones between the main tubes, the spacer zones being sealed relative to one another, cutouts made at an end of certain main tubes, in contact with the reflective layer, and/or secondary tubes positioned in the main tubes and/or in the spacer zones, the cutouts and/or the secondary tubes being configured to generate acoustic cells of different dimensions from identical main tubes.

Abstract: An aircraft tank device for increasing a flight range and a wing area of an aircraft includes a fairing which is formed and configured to at least partly cover an aircraft wing-aircraft fuselage intersection, to store a fuel, and to provide a lifting function. An aircraft including such an aircraft tank device is also disclosed.

Abstract: An aircraft with an aircraft fuselage, and a passenger cabin and a cockpit, where the aircraft includes a center-forward attendant space between the passenger cabin and the cockpit. A cabin crew member of the aircraft can stand in the center-forward attendant space for monitoring progress of an emergency evacuation of the aircraft. The aircraft has one or more emergency exits for providing egress of passengers from the aircraft fuselage during the emergency evacuation. The aircraft also has a situational awareness monitoring (SAM) system for use in evacuating the passengers from the aircraft during the emergency evacuation. The SAM system includes one or more imaging devices and one or more display modules, each of which displays within the passenger cabin images captured by a corresponding one of the one or more imaging devices.

Abstract: The system includes a closing module removably fastened to one end of the articulated arm of the door with which a door leaf is articulated, a closing module removably fastened to a structure rigidly connected to the door frame and a locking device removably fastened to the articulated arm. The closing module is able to alternately pull the closing module towards itself to move the door leaf into the closed position, and to move the closing module away from itself to move the door leaf into the open position. The locking device allows the locking lever to be moved alternately into the unlocked position to unlock the door leaf and into the locked position to lock the door leaf. The system enables the door of the aircraft to be closed remotely.