Abstract: An interface device between an injection tube and a mold provided with an injection hole, wherein the interface device includes a terminal element for an injection tube, with an end piece inserted into one end of the tube and a sealing ring that slides onto the tube, and a mechanism for holding and clamping the terminal element. The mechanism which is to be screwed into a mounting that is rigidly connected to the mold and is arranged around the injection hole, forms a seal between an injection end of the end piece and a sealing surface of the mold at the injection hole. The dismantlable assembly includes a screw-on socket that has a supporting surface for the sealing ring.

Abstract: A connection assembly of an engine pylon underneath an aircraft wing, the wing being provided with a fitting, the engine pylon being provided with a fork joint nested in the fitting and fixed to the said fitting by means of a traversing pin system, including: an external primary pin, a secondary pin mounted inside the primary pin, a primary shoulder mounted directly around the primary pin, at a blind end of the pin system, to block the said pin in translation, a secondary shoulder mounted around one end of the secondary pin, at a blind end of the pin system, to block the system in rotation, and an interlocking assembly mounted around the primary pin and the secondary pin, at a free end of the pin system, to block the pin system in translation.

Abstract: A cooling unit in a transport unit includes power electronics; a heat exchanger for thermally coupling a cooling agent of a central cooling system of the transport unit with air of the cooling unit to cool one or more generating devices; and a heat pipe for heat dissipation of the power electronics. At a first portion of the heat pipe, at least some of a working agent is in the liquid phase and, at a second portion of the heat pipe, at least some of the working agent is in the gas phase. In the first portion of the heat pipe, heat from the power electronics is absorbed by evaporating the working agent in the liquid phase. In the second portion of the heat pipe, heat is released to the cooling agent by condensing the working agent in the gas phase.

Abstract: Aided preventive diagnostics of an aircraft system, comprising a plurality of subsystems at least one of which comprises a subsystem configured for monitoring and notifying a detected event, using critical event charts. After receiving a message notifying the occurrence of said detected event, a minimal diagnostic set relative to said at least one detected event, comprising a plurality of elements each represented by a node of said critical event chart is created, each element of said minimal diagnostic set being determined according to at least one logical implication relation of said critical event chart with a node representing said at least one received notification message. At least some of the elements of said minimal diagnostic set are then ranked, said ranked elements forming part of said diagnostic report.

Abstract: Aided analysis of the failure tolerance of an aircraft system, comprising a plurality of subsystems at least one of which comprises a monitoring unit and notification of a detected event, using critical event charts. After selecting at least one receivable notification message represented by a node of the critical event chart, elements of the minimal diagnostic set capable of resulting in the generation of the at least one selected notification message are identified, the identified elements forming part of the failure tolerance report.

Abstract: The invention relates to a structural frame made from a composite material. The purpose of the invention is to obtain a structural frame with high mechanical performances while remaining simple in construction. This purpose is achieved in arranging sets of single-directional fibers in the main part of the structural frame at a predetermined angle. This system may be used as a structural frame particularly for an aircraft fuselage.

Abstract: A maintenance system for generating maintenance instructions for at least one system, the maintenance system having a plurality of system components set up to receive operating data for a system from a central control unit of the system, to use said data to identify a fault of a system component, to compare the fault with predefined known faults and to retrieve maintenance operations which have already been carried out or are predefined and are correlated with the known faults from a main memory and to select a maintenance operation which correlates with the identified fault in order to rectify the fault and to output the operation as a maintenance instruction. A method for planning maintenance operations has steps of monitoring the systems for faults and generating a maintenance instruction.

Abstract: A method and a device for the computer-assisted generation of a construction plan for modular aircraft components on the basis of already validated partial module construction plans for the individual modules wherein at least one element is assigned to a respective partial module construction plan, and in this manner a hierarchy is defined that comprises a higher, module level and a lower, element level, with the method comprising: re-utilizing at least one of the already validated partial module construction plans; depending on user input, re-specifying at the element level one of the at least one element in one of the partial module construction plans to obtain an individualized partial module construction plan; validating, only at the module level, a combination of one of the partial module construction plans with the individualized partial module construction plan; and in the case of successful validation, composing the partial module construction plans of the combination validated in this manner, to obta

Abstract: A method of developing maintenance optimization model includes finding relevant criteria to drive the design towards operational performances at minimal cost for the end user, selecting inputs necessary to assess criteria selected, defining mathematical models to jointly drive the equipment/sub-system/system design and its support towards better supportability, and presenting the maintenance optimization model results to enable the exploration of the cause and effect relationships between design decisions and their operational and support impacts. The selected inputs may cover all the potential factors influencing the criteria values. The mathematical modeling can facilitate leveraging the intuitive “cause and effect” relationship between design and support, and affordability.

Abstract: The present invention relates to an arrangement for adapting the transportation behavior of material to be conveyed, which arrangement comprises a first container, which is coupleable to a first pressure level; a second container, which is coupleable to a second pressure level; a connecting line for transporting material to be conveyed from the first container to the second container; and a pressure reduction device by means of which a pressure difference between the first container and the second container is controllably variable.

Abstract: A panel assembly for an aircraft including a panel having an upper aerodynamic surface and a leading edge, and a hinge fitting connected to an underside of the panel, defining a hinge line for the direction of rotation of the panel. The upper surface of the leading edge has an arcuate portion centered about the hinge line, and has an upturned portion forward of the arcuate portion. The panel assembly is pivotally connected to its hinge fitting to the trailing edge of the fixed wing portion and rotatable between a first position wherein the upper surfaces of the fixed wing portion and the panel are substantially flush, and a second position wherein the panel is rotated downwardly from the first position. A seal member attached to the trailing edge of the fixed wing portion, has a lower surface which seals against the upper surface of the panel during its movement.

Abstract: The invention relates to a lighting device and a method for illuminating a projection area based on a plurality of different lighting patterns. The lighting unit is controlled based on lighting data, which are received from an external central system via an interface, or stored in a memory unit. In this way, a plurality of different lighting patterns can be realized, so that at least up to four reading lamps can be replaced by a single lighting unit.

Abstract: A method and a device for filtering diagnostic messages obtained from a plurality of elements of a system, each of these elements comprising diagnostic means capable of detecting a failure and of transmitting a message comprising at least one failure indication. The state of at least certain elements of the said plurality of elements is represented by a model of state. After at least one failure message has been received, this message is filtered according to the failure indication that it contains and according to the model of state. In response to the filtering step, the model of state is updated according to the failure indication or the message is rejected. The filtering step is advantageously based on a propositional logic mechanism.

Abstract: A floor segment for a transportation system, in particular for an aircraft, for the spatial separation of an interior space of the into a lower space and into an upper space. The floor segment has an upper partition and a lower partition, which together with the upper partition encloses a hollow space, which is equipped for accommodating system component of the aircraft. Preferably, the floor segments are of a modular design so that within a floor individual floor segments can be exchanged for other floor segments that comprise identical or compatible dimensions and connections for the system components.

Abstract: A device for delimiting a crew rest area in an aircraft passenger cabin includes a curtain which is adapted to separate at least one seat disposed in the aircraft passenger cabin from a region of the aircraft passenger cabin surrounding the seat. In addition, the device includes a fastening device for fastening the curtain in the aircraft passenger cabin. At least a first part of the fastening device is fixed to a grip rail intended for installation in the aircraft passenger cabin or formed integral with the grip rail intended for installation in the aircraft passenger cabin.

Abstract: An aircraft frame and a method for obtaining an aircraft frame, which frame is made of composite material, and which frame comprises several partitions (20) that form, when joined, the aforementioned frame in its entirety, with these partitions (20) comprising sections (1) with a length (2), and sections (1) that are being arranged on the inside of the skin (3) that forms the fuselage of the aircraft. This fuselage is integrally embodied in a single piece, with the length (2) of the sections (1) being the maximum possible, In such a way that the maximum separation (5) between the frame section (1) and the skin (3), with the separation (5) being measured by the inside of the aforementioned skin (3), is lower than the limit value permitted for the use of a liquid sealant.

Abstract: According to one embodiment, a modular aircraft includes a propulsion module dedicated to flight, combining avionic equipment—wing structures assembly, flight deck, engines, tail unit—and a module dedicated to the carriage of passengers and/or goods. These modules include external cells extending longitudinally along a main axis and having tubular end parts of the same outline in the region of two disconnectable-coupling structures, one axial-coupling structure for keeping an end face of the propulsion module against an end face of the carriage module, and one radial-coupling structure for keeping an end face of the propulsion module against an end face of the carriage module. The wing structures assembly of the propulsion module includes two wing structures having opposite sweeps which are connected at the end and by a longitudinal connecting spar.

Abstract: Optimization of structures subjected to hot gas streams. The invention refers to a fairing (10) for aircraft horizontal stabilizer (3) comprising a front part (11) and a rear part (12), the front part (11) covering a limited extent of the fairing (10) surface, which is the part of the fairing (10) receiving hot air stream (6) coming from the aircraft engines (4), this front part (11) being made of an anti-erosion material, the rear part (12) covering the rest of the surface of the fairing (10), this rear part (12) being made of a material resisting the aerodynamic loads existing on the fairing (10). The invention also refers to an aircraft comprising a horizontal stabilizer (3) with a fairing (10) such as the one described.

Abstract: A covering of a fuselage for aircraft having propeller engines, including an opening which is surrounded by a structural frame formed by ribs and stringers of the aircraft around the area of maximum acoustic impact of the propeller engines. The opening further includes a non-structural panel joined to the structural frame by a non-rigid joint which considerably attenuates the vibrations through such joint, thus reducing the indirect acoustic noise and the indirect structural noise generated by the propeller engines inside the passenger cabin of the aircraft.

Abstract: A floor section for a vehicle cabin includes juxtaposed profiled elements of identical cross section. Each profiled element includes a mainly planar elongated cross member and a generally flat elongated panel. The cross member includes a lower stiffener, is positioned in a transverse vertical plane, and is attachable at two extremities to a vehicle frame. The elongated panel is positioned in a horizontal plane and includes an overlap region along one longitudinal edge and a bearing region along another longitudinal edge. The overlap region and the bearing region are of similar width and of total thickness less than or equal to a mean panel thickness. The panel is perpendicular to the cross member, and a bearing region underside is coplanar with a lower face of the elongated panel and is secured to the cross member at two or more points substantially in line with a middle of the bearing region.