Abstract: A device for moving an object on a rail that has grid openings, the device having at least one first movement element, at least one first drive element, and at least one engagement element for engaging at least one grid opening. The engagement element is positioned on the first movement element. The first drive element for driving the first movement element is connected to the first movement element, and the first movement element is movably held in such a way that the engagement element is at least in some regions guided along an outside of the device. As a result of this an even force is directly introduced into the rail to prevent the object to be moved by sliding becoming skewed or jammed. Likewise, the device can be supplemented by a motor so moving the object can be carried out automatically, precisely, and quickly.

Abstract: Diagnostic system including a sensor device with a sensor for generating signals corresponding to a first operational condition, a control device with a timer and function for performance of measurements, and a signal transmission device. The system includes a device for determination of a second operational condition of the system component and configured where the sensor value of the signal transmission device corresponding to the first operational condition is furnished when the sensor value corresponding to a second operational condition of the transmission mechanism is higher or lower than a comparative value, and housing component of a lubricant container and in particular closure device for sealing an opening of such a housing component from a lubricant which is present in the operational use thereof in an internal space thereof, having arranged therein: at least one sensor device comprising at least one sensor for determining the water content in the lubricant.

Abstract: An aircraft wing cover (10) comprising an integrally stiffened sandwich panel including first and second skins (11, 12) sandwiching a core layer (13), wherein at least one of the skins has a plurality of spanwise extending integral regions of increased thickness (18) accommodated by corresponding regions (19) of decreased thickness in the core. Also, a method of fabricating an aircraft wing cover, and a method of designing an aircraft wing.

Abstract: The aircraft includes at least one engine having contra-rotating rotors, the engine or at least one of the engines having imbalances associated with at least one ellipse. The aircraft includes a means capable of controlling the engine or at least one of the engines such that, at a given engine speed, the large axis of the ellipse or at least one of the ellipses extends in a direction for which the vibrations generated by the engine or engines have a minimum intensity in at least one predetermined site, particularly in a predetermined area, of the aircraft.

Abstract: A holding device for a mounting part installed inside an aircraft fuselage includes an anchor plate configured to attach the holding device to a support rail of the aircraft fuselage and including at least one engagement section. The holding device further includes a holder module separably connected to the anchor plate and configured to fix the mounting part to the aircraft fuselage and having a hook section configured to positively engage the at least one engagement section so as to fasten the holder module to the anchor plate, and at least two clamping blocks disposed on the holder module.

Abstract: A ventilation system for ventilation of an aircraft area includes a ram-air duct with an air inlet, a first ram-air duct branch and a second ram-air duct branch parallel to the first ram-air duct branch. A supply line connected to the ram-air duct is adapted to supply air flowing through the ram-air duct to the aircraft area to be ventilated. In the first ram-air duct branch a conveying device is arranged. In the second ram-air duct branch a heat exchanger of an aircraft system to be supplied with cooling energy is arranged. The ventilation system provides ventilation to the aircraft area during ground operation without requiring the conveying device to flow air through the heat exchanger.

Abstract: The wiper blade for a surface of the type with a dual curvature, the wiper blade including a flexible blade element and a means of applying a pressing force to at least one point of the blade element in a direction Z mostly normal to the surface, also including means of varying the pressing force over time, at least some of the points, between pre-chosen positive and negative limit values, and means of commanding the pressing force. These means for bringing about local pressure or lift are electromagnetic.

Abstract: A screwing device includes a threaded hole that extends from an insertion opening to an end of the screwing device, which end is opposite the insertion opening. In the region of the insertion opening a first radial sealing element is arranged that by way of the insertion opening extends outwards in an axial direction of the hole. Spaced apart from the first sealing element in an axial direction of the hole a second radial sealing element is arranged in the screwing device with the internal diameter of the second radial sealing element being smaller than the external diameter of the threaded hole. In this manner a screwing device may be provided that is self-locking, exchangeable, and fluid-proof and that is suitable especially for vehicles and in particular for aircraft.

Abstract: A system for air conditioning an aircraft cabin includes an air conditioning unit connected to a central mixer in order to supply the central mixer with air at a desired low temperature. A first recirculation system is designed to remove exhaust air from a first aircraft cabin region and is connected to the central mixer in order to lead the exhaust air into the central mixer. A second recirculation system is designed to remove exhaust air from a second aircraft cabin region and is connected to first and second local mixers in order to lead the exhaust air into the local mixers, the local mixers also receiving mixed air flow from the central mixer. The second recirculation system includes a cooling unit which is designed to cool the recirculation air removed from the second aircraft cabin region before delivery to the first and second local mixers.

Abstract: An aircraft nacelle includes a cowling, an engine housed in an internal volume of the cowling, and at least one thrust reverser, an air passage duct being formed between an internal wall of the cowling and an external wall of the engine. The cowling includes a fixed cowling part and a moving cowling part that is translationally movable between a plurality of positions, at least one of the positions varying an air flow through the duct. The moving cowling part includes the at least one thrust reverser so that translational movement of the moving cowling part also allows the moving cowling part to switch from a position in which the at least one thrust reverser is retracted into a reverse-thrust position in which a bypass flow is deflected to generate a reverse thrust.

Abstract: A link device for safety linking of a first member to a second member includes a first element, a second element, and a fluidic vibration transfer mechanism. The first element includes a first link end adapted to be directly linked to the first member, and a second link end adapted to be directly linked to the second member. The second element has a first link end adapted to be directly linked to the first member, and a second link end adapted to be directly linked to the second member. The fluidic vibration transfer mechanism links the first and second elements of the link device to one another, and includes at least two pressure chambers filled with a pressurized liquid, separated by at least one piston integral with the first or second element.

Abstract: A device for lying or sitting on includes a frame and also a covering which is stretched over the frame and defines a surface for lying or sitting on of the device for lying or sitting on. A tensioning device is adapted to interact with the frame and/or the covering in order to vary the pre-tensioning force which acts upon the covering.

Abstract: A method of forming a hybrid component comprising at least two metallic parts, the method comprising preparing a first metallic part by forming at least one macroscopic interfacing feature on an interfacing surface of the part; positioning the first part in a mould tool; introducing a metallic powder into the mould tool and around the interfacing feature(s); and consolidating the metallic powder by a Hot-Isostatic Pressing (HIP) process to form a second metallic part which encapsulates the interfacing feature(s) to provide a mechanical connection between the first and second parts of the component. Also, a hybrid component so formed. The metallic parts may have substantially different material properties.

Abstract: The invention relates to a secure access airlock enabling the communication between several rooms of an aircraft, the secure airlock being installed in an area of the aircraft between a first room and at least one second room, characterized in that it includes two mobile partitions provided in the form of portions of concentric cylinders, each of the partitions being capable of being moved, separately from one another, about a common axis, so as to provide a single opening therebetween which makes it possible to access either of the rooms, the two partitions being capable of moving over two concentric cylinders having different diameters.

Abstract: A curable assembly which upon the application of curing conditions will form a completed component or part component comprises two pieces of composite fiber-reinforced, resin matrix material, with filler component of relatively rigid material arranged therebetween. The intermediate component is arranged to be secured between the two pieces. The filler component has a body with first and second opposing surface profiles. The filler component can be used to transmit or react a consolidating load during curing.

Abstract: A method of joining a first component to a second component, the method comprising forming an array of projections extending from a bond surface of the first component, the projections having a plurality of different profiles; and embedding the array of projections in the second component formed of a plurality of laminate plies, wherein each projection profile is adapted to best transfer load into a respective one of the laminate plies. The resultant joint is able to transfer load more progressively between the two components leading to improved tensile strength.

Abstract: The invention relates to a production method for producing seamless, integral aircraft fuselage sections. The method comprises the following steps: a) application of a first vacuum film to a stable winding core and evacuation of the first vacuum film, b) depositing of the fuselage section in layers on the winding core by wrapping the same, c) application of an outer mold that is unstable compared to the stable winding core, to the fuselage section, wherein the winding core stabilizes the outer mold, d) application of a second vacuum film to the outer mold, e) aeration of the first vacuum film and evacuation of the second vacuum film in order to draw the fuselage section closer to the outer mold and detach it from the winding core at least in one region, a) curing of the entire arrangement in an autoclave to produce the finished fuselage section.

Abstract: The system includes deflection transmission means (16) to provide a deflection position of the high-lift device (8) for each setting angle position of an adjustable HTP (2). Preferably, the deflection transmission means (18,20,23) comprise essentially of a mechanical linkage connected between the high-lift device (8) and the aircraft (1).

Abstract: A flight control system for an aircraft, intended for controlling a plurality of actuators adapted for actuating control surfaces of the aircraft from information supplied by piloting members and/or sensors of the aircraft. The system includes a primary control system adapted for controlling a first set of control surface actuators and a secondary control system adapted for controlling a second set of control surface actuators, the primary and secondary systems being respectively powered by independent energy sources of different types.

Abstract: In the case of a fiber composite component for energy absorption in the event of a crash for an aircraft or spacecraft, the fiber composite component is formed as a laminate construction made of CFRP layers and at least one integrated metal foil portion which is corrosion-resistant with respect to the CFRP layers. A fuselage structure portion of an aircraft or spacecraft is formed using at least one fiber composite component of this type. An aircraft or spacecraft comprises a fuselage structure portion of this type.