Abstract: The invention relates to an improved aircraft electronics cooling system for an aircraft having a liquid cooling system (2), the aircraft electronics cooling system providing a thermal coupling between an electronic device (40a, 40b, 40c, 40d, 42, 44) to be cooled and the liquid cooling system (2) of the aircraft. A coolant delivered by the liquid cooling system (2) may flow through a board of the electronic device (40a, 40b, 40c, 40d), through a heat sink on which the electronic device (42) is arranged and/or through a housing in which the electronic device (44) is arranged. The coolant may be permanently in the liquid state in a cooling circuit. The coolant may vaporize at least partially while cooling the electronic device.

Abstract: Until now, an orientation pattern has been projected onto the skin by means of lasers. The stringers provided with an adhesive film are then positioned by hand on the skin and fixed by pressure weights. A precision of ±3 mm is thus achieved. The fine positioning takes place by means of comb templates. The templates are set one after the other, pressure weights being removed from the stringers after each setting, so a manual orientation of the stringers is made possible. The weights are then set again. The imprecision is still ±1.4 mm. This procedure is very time-consuming and not precise enough. It is therefore proposed to use a gantry robot with a gripper beam to position the stringers, the gantry robot cooperating with a loading unit and a heating station. The time spent is thus substantially reduced and the precision of the product is decisively increased.

Abstract: A system is provided that combines an oxygen enrichment device (OBOGS) for generating oxygen-enriched air with a fuel cell system that includes, but is not limited to a fuel cell for using the oxygen-enriched air as a reaction gas within the fuel cell, as a result of which the output of the fuel cell is improved while the size and weight of the fuel cell remain the same.

Abstract: A system for production which includes a database configured to store information about technical events and a server to provide centralized management of the information. The database is configured to be accessed by several end-users connected to the database via a network. A web-based graphical user interface is configured to display, at the end-user, quality assurance information relating to the technical events associated with the production of aircraft and aircraft-related components.

Abstract: A computer-aided method of obtaining a preliminary ply model of a composite component to be used in the manufacture of industrial parts by stacking and joining a plurality of plies of composite materials, comprising the following steps: a) obtaining from stress calculations a ply stacking sequence for the component subdivided into panels; b) automatically generating a stacking table containing the ply sequence for each different zone (defined by its ply sequence); c) automatically generating a grid table; d) optimizing said stacking table; e) performing the plies drop-off distribution by means of a tool that allows carrying out said distribution automatically according to a predetermined staggering rule; f) obtaining an output table containing the data required for representing the ply model in a CAD program.

Abstract: The invention relates to a deflector for an aircraft, comprising a discharge pipe for leading a fluid to be drained from the aircraft by way of an outlet end to the environment of the aircraft; an actuator, coupled to the discharge pipe, for swinging out, when required, the discharge pipe to at least one activation position, wherein in the activation position the outlet end is arranged so as to be spaced apart from the exterior skin of the aircraft, and the deflector guides the fluid to be drained so that it exits outside a flow boundary layer that is present on the exterior skin. The deflector according to the invention is activated when required and is able to discharge structure-damaging fluids to the environment in such a way that the exterior structure of the aircraft does not become wet, and at the same time the deflector according to the invention, normally accommodated within the contour of the aircraft, does not result in any additional aerodynamic resistance.

Abstract: A wing box rib (13), joining an aircraft wing (3) to the wing box and to the rest of the structure, extends advantageously over an adjacent part of the fuselage (2), having in particular an upper line (14) situated above a junction line (15) of the wing upper surface panel (3). The connection is simplified, as is the structure of the aircraft and its manufacture, a lightening is possible, and the transmission of stresses takes place in a more favourable manner.

Abstract: A method of routing the physical links of a avionics platform inside an aircraft. A physical link connects a plurality (N) of equipment units and is composed of one or more branches, where each branch of the link connects a sender equipment unit to a receiver equipment unit. The method makes it possible to minimize the total cabling length of the platform and, where applicable, to choose among various positions of the equipment units inside the aircraft and/or various routing graphs.

Abstract: The present invention relates to a device and a method for providing cut-to-length rovings having a defined length from an endless roving, in particular in the aviation and aerospace sector, and also to a machine with a device of this type. The device comprises a loop shape setting arrangement, a loop bracing arrangement and a cutting arrangement. An endless roving can be braced by means of the loop bracing arrangement onto the loop shape setting arrangement, thus forming a loop which can be cut to length by means of the cutting arrangement in order to produce the cut-to-length roving.

Abstract: An aircraft fuselage with a shape elongated along a longitudinal axis X along a longitudinal axis of the aircraft that determines a direction toward the front along a direction of motion of the aircraft in flight. A front section with straight cross sections widening relative to the X axis, located at the front of the fuselage and ending in the front of the fuselage in a fuselage nose, and delimited at the rear by a cross section for joining to a rear part of the fuselage behind the front section. The front section includes a cockpit located above a floorboard between a cockpit bulkhead to the rear and a front base to the front.

Abstract: An on-board telecommunication system, partitioned into a secure area and a non secure area, including at least a first telecommunication equipment unit in the secure area, a second telecommunication equipment unit in the non secure area, and a first one-way link from the first to the second equipment. The first equipment unit is configured to transmit data on the first link according to a first protocol. The system further includes a second link from the second to the first equipment unit, in accordance with a second protocol, the first two layers of which are distinct of those of the first protocol, the second equipment configured to transmit data on the second link as messages in accordance with the first protocol and encapsulated in frames in accordance with the second protocol.

Abstract: An aircraft control surface mounting structure including a cantilever rib mounted to a spar, the rib includes a first arm and a second arm both orientated to be substantially parallel to the line of flight of the aircraft.

Abstract: An insulating mat for the sound insulation of an aircraft fuselage structure that is composed of frames and stringers extending transverse to the frames, to a fastener means for fastening an insulating mat on an aircraft fuselage structure such that acoustic bridges are prevented. An insulating kit is also provided that comprises at least one insulating mat as well as at least one fastener. The insulating mat features a plurality of fastening clips that are fixed on a first surface of the insulating mat and laterally protrude over the border of the insulating mat.

Abstract: A support for an optical fiber partially submerged in a substrate is discloses in which the support is arranged with fiber fixing means for fixing a portion of the fiber to the support so that strain on the portion of the fiber external to the substrate and support member is at least partially diverted from the portion of the fiber internal to the support member.

Abstract: An aircraft engine mounting structure comprising a pylon box having an upper surface and at least one attachment element configured to be attached to a front spar of an aircraft wing box, the front spar having a lower surface, the attachment element being configured to attach the rear face of the pylon box to the front spar such that at least a portion of the upper surface of the pylon box lies above the lower surface of the front spar.

Abstract: The system for defrosting the leading edge sheath of an air intake hood for a turboengine comprises a hot pressure air supply duct (60) and a protective shell (90) which are longitudinally rigid and rigidly fixed to the partition (5) of a caisson (10), wherein said protective shell (90) is slidable with respect to a sliding bearing (15) embodied in the partition (11) and said air supply duct (60) is connected to the protective shell (90) by an elastic wall (16) closing an insulating space (12) and enabling relative longitudinal movements to be carried out between the air supply duct (60) and the protective shell (90).

Abstract: A carrying system for receiving containers in a vehicle includes at least one container, at least one electrical consumer arranged in the container, at least one primary winding in a first core and at least one secondary winding in a second core. The secondary winding is arranged in the container, and the primary winding can be attached on the vehicle side in such a manner that movement of the container to a receiving position results in alignment of the primary winding and the secondary winding. The primary winding and the secondary winding are adapted for inducing in the secondary winding an alternating voltage that is applied to the electrical consumer.

Abstract: An aircraft landing gear including a leg, a bracket which defines the axis of rotation of the leg on the operating plane defined by the leg extension and retraction positions and a leg operating device consisting of at least one strut whose first end is provided with a first means for connecting to the landing gear element and second end is provided with a second means for connecting to the element of the gear-receiving landing gear casing for which the at least one strut expands outside of the operating plane of the gear leg.

Abstract: A method and apparatus is disclosed in which an aircraft landing system is at least partly primarily powered by power provided by a ram air turbine (RAT).

Abstract: The invention relates to aircraft noise reduction apparatus, in particular, but not exclusively, to noise reduction apparatus on an aircraft landing gear. The aircraft noise reduction apparatus comprises a noise reduction attachment for a landing gear of an aircraft. The noise reduction apparatus is movable between a first position in which it deflects air away from a noise inducing component of the landing gear and a second position in which it allows access to the noise inducing component. The movement of the noise reduction attachment between the first and second positions is actuated by a part of the landing gear.