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: 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 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 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 module for an aircraft has a fuselage structure and a floor element defining a floor plane. The module includes a frame device adapted for mounting a functional element and the frame device is adapted for attachment to the floor element of the aircraft at a first location in the floor plane.

Abstract: An avionics module including an electronic circuit board, a case in which the circuit board is positioned and including at least one inlet orifice and at least one outlet orifice for cooling air, a first corridor for the circulation of the cooling air formed between a first face of the circuit board and a first facing wall of the case, and a second corridor for the circulation of the cooling air formed between a second face of the circuit board and a second facing wall of the case. The module includes at least one baffle for controlling the distribution of the cooling air between the first and second corridors. Preferably, the baffle is fixed to the electronic circuit board.

Abstract: An aircraft panel, notably a fuselage panel of the aircraft, includes at least one opening equipped with a surround intended to accept a closing-off device that closes off the opening. The panel includes at least one exterior surface. The surround surrounding the opening is fixed to the panel, forming an interface for fitting the closing-off device, and includes at least one lip extending towards the center of the opening. The lip supports the closing-off device. The surround has an external face interposed between the exterior surface of the panel and the closing-off device. The surround includes fixing apparatus which works by gripping the edge of the opening of the panel.

Abstract: A holder for connecting a module to a component of an aircraft or spacecraft includes a first holder portion having a first adhesive face and a second holder portion having a second adhesive face. The first and second holder portions are movable relative to one another in an initial state of the holder such that a portion of the component can be received between the holder portions so as to glue the holder portions to the component by means of an adhesive layer in each case. The holder has two or more guided parts which are movable relative to one another by means of mutually cooperating guide faces in the initial state of the holder. The guide faces are suitably formed for being glued together using an adhesive. The holder can be used to counter peeling stress of an adhesive connection of the holder in the region of the first and/or second adhesive face.

Abstract: A method for accelerated drying of at least one polymer which is located at least partially on a component, in particular at least a layer of paint and/or a sealing agent which is applied to an aircraft component in particular with a different material composition, involving the following steps of: a) at least partially applying the at least one polymer, in particular an epoxy resin and/or polyurethane-based layer of paint and/or a sealing agent, to an upper side of the component, and b) at least partially drying the polymer by means of electromagnetic radiation with a wavelength range of between 0.28 ?m and 4.0 ?m. Accelerated drying of the polymer, in particular the paint layer thereby becomes possible from an upper side of the component to an upper side of the paint layer.

Abstract: A stiffened panel includes a panel at least one of whose surfaces is equipped with stiffeners each of which includes a base that is pressed against the surface of panel, as well as a core that is oriented orthogonally relative to the base and whose first longitudinal edge is integral to the latter. At least one of the stiffeners includes a multitude of notches that cross over a second longitudinal edge of the core opposite the first edge, so that they extend towards the outside of the stiffener.

Abstract: A system for detecting jamming and/or uncontrolled movement of an aircraft control surface includes first means for estimating the value of at least one parameter of an equation simulating the feedback loop dynamic of the control surface, according to a recursive autoregressive method with exogenous variable of RARX type in a recursive least squares way, and second means for detecting jamming and/or uncontrolled movement of the control surface, according to the estimated parameter value by the application of a decision test in the parametric space.

Abstract: A draining system having an odor seal for a vacuum toilet drain system in which a flexible hose acts as an odor seal. As a result of the flexible hose, propagation of odors can be prevented when the hose collapses flat, for example as a result of its intrinsic weight, and consequently there is no longer a flow-through cross section, wherein, however, drainage of liquids remains possible.

Abstract: A system for the drying of exhaust gases from a fuel cell system includes two heat exchangers alternately exposed to an exhaust gas, which ice and accumulate water vapour from the exhaust gas by cooling through a coolant. A valve arrangement with a number of valves is adapted in such a manner that it operates one of the heat exchangers in an icing phase, in which the icing of water vapour is conducted, and the other heat exchanger in a regeneration phase, in which the accumulated ice melts and is extracted, in an alternating manner. This system is especially suitable in aircraft for drying an oxygen depleted exhaust gas from a fuel cell system for inerting a tank.

Abstract: A beam (20) comprising first and second flanges (23, 24), the beam (20) having a first region (28, 30) extending between the flanges (23, 24) and a second region (26) extending between the flanges. The first region (28, 30) is designed to support an applied concentrated shear load and the second region (26) is designed to support a predominantly bending load. The first region comprises a fan-shaped truss comprising a hub (36) adjacent the first flange and a plurality of struts (37) which extend substantially radially from the hub (36), and the second region (26) comprises either a truss structure which is substantially regular in the longitudinal beam direction or a shear web. The beam may, for example, be used as a floor beam for an aircraft fuselage.

Abstract: Method and system for displaying meteorological phenomena encountered by an aircraft flying along a flight plan. The display system includes a display device configured to present on a screen a meteorological indicator, the meteorological indicator comprising a time line representing a time scale relating to the duration of the flight of the aircraft along the flight plan and, on this time line, a set of first symbols illustrating meteorological phenomena and a second symbol indicating the current instant.

Abstract: A lighting strike protection device for applying automatically to a fiber composite component. The protection device includes a reinforcement structure having a width that is less than a width of the metal strip. The fiber composite component having an integrated lighting strike protection.

Abstract: A habitation and sleeping module, in an aircraft, for accommodating at least one member of a flight crew, with the module having a first sleeping area. Furthermore, an ascent region is provided for ascending from a lower level into the module, wherein the ascent region includes an ascent device that is laterally arranged on the module.

Abstract: A method for the manufacture of a fiber-reinforced thermoplastic composite module from a multiplicity of module components, which are continuously moved in the feed direction and are connected together section-by-section by means of a pressure application head that can be traversed in the feed direction and in the counter-direction. A device for the execution of the method is also disclosed.

Abstract: A regulating system for the regulation of the cabin pressure PC of an aircraft, includes at least one cabin pressure regulator unit, which is so configured that, by controlling at least one air outflow or air inflow device of the aircraft, it can set the cabin pressure Pc within the aircraft fuselage with the latter supplied with fresh air and subjected to pressure at a pressure level or a cabin height defined by the cabin regulator unit. If there are changes to be made to the pressure level or the cabin height, for example while the aircraft is climbing or descending, the cabin regulator unit maintains the quotient of the time-related change of the cabin pressure Pc in the aircraft cabin and the cabin pressure Pc constant. The result is that the gas expansion rate, or the gas compression rate in a passenger's middle ear, remains constant, so that during the entire climbing or descending stage no varying or increasing discomfort is experienced by the passengers.

Abstract: A method and apparatus for producing a hollow component, in particular in the field of aviation or aerospace, including the following steps: provision of an inner contour closed along its circumference; laying of a fiber material over the inner contour; and curing of a matrix of the fiber material to form the component.