Abstract: A device for cooling and dehumidifying gases includes a first hollow body with a gas inlet, a gas outlet and a condensate drain; a second hollow body with a coolant inlet and a coolant outlet; and a drive unit. The first hollow body encloses the second hollow body at least in part. One of the first hollow body and the second hollow body is pivotally held relative to the other hollow body and includes at least one turbulence-generating body that extends in the direction of the other hollow body. For rotating the pivotally held hollow body the drive unit is couplable to the hollow body. In this manner a single-stage device for cooling and dehumidifying gases that include water vapor is implemented, which device requires little installation space and is of a particularly lightweight construction. Thus the device is particularly well suited for use in vehicles, in particular in aircraft.

Abstract: In one aspect of the method for displaying an image on a screen of a cockpit of an aircraft, control means: control a first display on the screen of an image comprising a background; and then control a second display so that, in at least one zone of the image that is determined independently of the background, the background presents a non-zero second mean luminance that is less than a first mean luminance that it presented during the first display. In another aspect, the control means control the display on the screen of an image comprising a background in such a manner, that at least in a zone of the image that is determined independently of the background, the background presents non-zero mean luminance that is less than mean luminance of the remainder of the background.

Abstract: An aircraft assembly is provided having a first aircraft component and a second aircraft component, at least one of the aircraft components being composed of a fibre-reinforced composite material, a connecting device connecting the first aircraft component to the second aircraft component, the connecting device including a first and a second section having a carrier element connected to the first and second aircraft components respectively, the first section having a first surface facing the first aircraft component and a second surface facing away from the first aircraft components, the second section having a first surface facing the second aircraft component and a second surface facing away from the second aircraft component. The first and second sections include a plurality of hook and loop elements extending from the second surface of the carrier element and cooperate to produce a hook and loop connection between the first and second aircraft components.

Abstract: An aircraft nacelle includes, on its outside surface, at least one opening that is blocked by at least one movable part (16) that is kept in closed position by at least one locking mechanism that connects the movable part (16) to another part of the nacelle (16?), characterized in that it includes an anchoring point (32) on one of the two parts (16?) that are to be connected, and a detachable link (34) that is connected to a traction element (36) that is integral with the other part (16) that is to be connected.

Abstract: A passenger seat system includes a backrest and a seat, which has a first sub-portion having a first surface and a second, opposite surface to the first surface as well as a second sub-portion having a first surface and a second, opposite surface to the first surface. The sub-portions are relatively movable in order to provide first and second operating positions. In the first operating position the sub-portions are positioned in relation to the backrest one behind the other such that the first surface of the first sub-portion and the first surface of the second sub-portion form a usable total seat surface. In the second operating position the sub-portions are positioned in relation to the backrest one above the other such that one of the surfaces of the first sub-portion or the first surface of the second sub-portion forms a usable partial seat surface.

Abstract: A cap has a body portion forming a central cavity, and an annular flange which extends outwardly from the body portion. The body portion is deformable between a first configuration in which the annular flange is inclined upwardly, and a second configuration in which the annular flange is inclined downwardly. A method includes applying a quantity of sealant to the annular flange in the first configuration; fitting the cap over the end of the fastener so that the fastener is enclosed by the cap; and turning down the annular flange such that the cap assumes the second configuration in which an annular pocket is formed between the flange and the base, and the sealant material fills the annular pocket; and bonding the cap to the structure with the sealant material.

Abstract: A method for edge sealing a fiber-reinforced component formed from a carbon fiber-reinforced thermoplastic or duroplastic plastic material includes electrostatic coating of at least one section of an edge of the component with a thermoplastic powder so as to form a powder coating; and fusing and cross-linking the powder coating in a furnace so as to create a smooth edge seal.

Abstract: A separation device is provided for a vacuum toilet system of an aircraft, which makes possible a significantly simpler type of cleaning, which can be done more quickly, of a profile separator. The movably held combination of a wiping device and the profile separator can carry out a relative movement. As a result of mechanical contact between the wiping device and the profile separator the deposits are removed from the profile separator.

Abstract: A double-skin nozzle system including an internal tube for transporting a liquid, formed by a plurality of tube portions connected to one another by removable junction systems, an external tube positioned around the internal tube and formed by a plurality of tube portions connected to one another by junction systems, wherein at least two junction systems each include a blocking device for blocking, along the external tube, the flow of a liquid coming from a leak from the internal tube, and at least one drain for removing the liquid coming from the leak from the internal tube.

Abstract: A pivot joint assembly has a first part with a hole. A pivot pin passes through the hole. A second part is carried by the pivot pin to be rotatable relative to the first part. A bush has an annular sleeve with an inner face engaging the pivot pin and an outer face engaging a bore wall of the first part. A sealing ring between the bush and the first part. The sealing ring has a body attached to the first part, and a sealing member extending away from the body in a radial direction to a sealing lip which engages the bush without being attached thereto. The sealing member is resiliently compressed to urge the sealing lip towards the bush to maintain engagement with the bush in the event that the bush moves away from the body in the radial direction.

Abstract: The invention concerns a pressure application roller unit 2 for the laying down of fiber strips 80 on a surface 82, with a pressure application roller 7 mounted in a mounting unit 35 such that it can rotate about a shaft 10. In accordance with the invention the pressure application roller 7 is subdivided into a multiplicity of roller segments 4, 6 arranged next to one another, which in each case are mounted in the mounting unit 35 such that they can be displaced. As a consequence of this configuration an optimal adaptability of the pressure application roller unit 2 to a surface 82 of a molding tool 84 that is curved in one or two dimensions is provided. By this means the pressure application roller unit 2 can be guided by means of a robot arm 102, even over molding tool surfaces that are more highly spherically curved in some sections.

Abstract: An aircraft fuselage frame assembly includes a first lower frame element having a cross member and a curved fuselage tub frame. A second upper frame element of the assembly has a cross member and a curved upper frame segment. A third frame element of the assembly is made of a cross member section, floor strut section and frame section. The third frame element is formed as a single, integral triangle element having a hypotenuse that is curved to adopt a curvature of the aircraft fuselage and joining portions at angle areas of the triangle. A lower frame link is joined to the first upper frame and at a first angle area of the triangle element; an upper frame link is joined to the second upper frame and at a second angle area of the triangle element; and a floor cross member is joined at a third angle area of the triangle element.

Abstract: A method for the manufacture of a fiber-reinforced component includes heating a blank of a carbon-fiber-reinforced thermoplastic plastic material to at least a melting temperature of the thermoplastic plastic material; introducing the blank into an at least two-part molding tool; forming the fiber-reinforced component by applying pressure on the blank using the molding tool; and injecting a further thermoplastic plastic material into at least one edge region of the molding tool so as to form an edge seal.

Abstract: An aircraft monument for installation in an aircraft cabin comprising a first functional module, a second functional module and a side wall for delimiting the first module from at least one of a region of the aircraft cabin adjacent to the first module and a region of the aircraft monument adjacent to the first module. The side wall is movable between a first and a second operational position and comprises a first side-wall region separating the first and second functional modules and in the second operational position, the side wall is displaced in the direction of the second module relative to its position in the first operational position, so that a movement of the side wall from its first operational position into its second operational position results in an enlargement of a base area of the first module and a corresponding diminution of a base area of the second module.

Abstract: The invention discloses a trailing edge (2) of an aircraft aerodynamic surface, which comprises an upper skin (6) and a lower skin (7), being the upper and lower skins (6, 7) made of composite material. In the trailing edge (2) a lightweight part (1) is assembled at an end section (13) of the upper and lower skins (6, 7). The lightweight part (1) is covered by a metallic sheet (8), and has a “V”-shaped cross section with arms and peak, where the peak of the “V”-shaped cross section has a rounded shape and is located opposite the end section (13) of the upper and lower skins (6, 7).

Abstract: A data processing and display system includes processing and display means adapted for displaying, from a more secured domain and on a same screen of a display processing device, information data from one or more less secured domains and active data from the more secured domain as a superimposition.

Abstract: A system for opening and closing a door for a landing gear compartment of an aircraft includes a connection between the landing gear and the door with a first system forming an actuator mounted on the landing gear and a second system forming an actuator mounted on the door. The two systems form actuators connected to each other by at least one fluid communication device such that actuating the first system causes the actuation of the second system.

Abstract: A conduit harness retention system has a base, a first spacer, a second spacer and a cap which snap-fit together to retain P-clip harnesses in position spaced from an aircraft fuselage.

Abstract: A method for producing a fiber composite component, in particular for aerospace, the method comprising the following steps: forming a mold core from a material comprising cork by a molding tool to establish an outer geometry of said mold core; arranging the so formed mold core adjacent to an at least partly hardened stiffening element on a base element of said composite component to be produced for the shaping of at least one molded portion of said fiber composite component to be produced; and multistage exposure of at least said molded portion to heat and/or pressure to produce said fiber composite component; a corresponding mold core and a corresponding fiber composite component.

Abstract: A tank module for an aircraft is designed for being fitted into the aircraft fuselage from outside. The tank module comprises at least one receptacle and a shell section that forms an outer end of the tank module and is connected to the receptacle. The shell section can be fitted into a fuselage opening in such a way that the receptacle is positioned in the interior of the aircraft fuselage.