Abstract: A method for detecting the opening of a thrust reverser for a jet engine of an aircraft is disclosed. According to the method, an operating parameter of the turbojet (1) is determined being responsive to the opening of a mobile element (2a, 2b) of the thrust reverser and reacting to such an opening by a sudden variation of the value thereof, the parameter is measured continuously and the mobile element (2a, 2b) is considered as being opened when the sudden variation is detected.

Abstract: A device for mechanically linking with a rotating axis at least two parts, which is configured to extend in a longitudinal direction in coaxial bores formed respectively in the at least two parts hinged in relation to each other around the axis. The device includes: a cylindrical body including at least one end portion including at least one longitudinal slot, the cylindrical body including in the longitudinal direction a cylindrical bore extended by a frusto-conical bore extending in the at least one end portion configured to be located in another bore; an insert of frusto-conical shape substantially complementary to the frusto-conical bore, the insert including a tapped aperture extending in the longitudinal direction when the insert is accommodated in the frusto-conical bore, and a screw with a threaded end configured to cooperate by screwing with the tapped aperture of the insert allowing to lock the cylindrical body in the another bore and making a rotoide joint around axis.

Abstract: An installation of systems in aircraft fuselages such as thermophonic insulation mattresses and devices such as onboard systems, and bundles of electric wires or fluid ducts (air, water, oxygen, hydraulic fluid). A structure for fastening onto an aircraft fuselage includes at least frames and stringers, the structure further including: fuselage stabilizers connecting the frames and stringers, wherein two stabilizers of two consecutive frames face each other between the two consecutive frames; and a strip board connecting the two stabilizers and including a fastening mechanism arranged so as to receive corresponding fastening mechanisms of the insulation mattresses and the devices.

Abstract: A device for controlling engine speed of a multi-engine aircraft includes a series of components for automatically controlling the speed of the engines during the take-off, so as to avoid discrepancies in the engine speeds. To this end, as long as all engines of the aircraft do not have, at least at given intermediary moment of the take-off, a driving parameter value equal to a preset intermediate value of the parameter, the speed of all of the engines cannot exceed an intermediate speed associated with the preset intermediate value. Thus, all engines must reach the intermediate speed so that the acceleration to a higher take-off speed can continue simultaneously for all engines.

Abstract: A tail-cone of an aircraft includes a skin provided with a movable fairing which, by a swing articulated mechanism, is supported on the skin in order to allow the opening/closing of the movable fairing and gain access to the inside of the tail-cone. The tail-cone includes actuators for operating the swing articulated mechanism in order to permit the automatic opening and closing of the movable fairing to be carried out.

Abstract: A trajectory analysis device automatically determines an auxiliary takeoff trajectory including a curvilinear lateral profile, which allows to maximize the takeoff weight of the aircraft. To this end, the device includes an initial data generation device, an auxiliary takeoff trajectory determination device, and a display device. The crew of the aircraft may then review the optimized auxiliary takeoff trajectory.

Abstract: A door for an aircraft engine nacelle, comprising an opening leaf, locking device with which the opening leaf may be locked in the closed position, as well a device for setting the opening leaf into motion with which the latter may be displaced from the closed position to the open position. The locking device has a mechanical fuse intended to break under the effect of a force exerted by the opening leaf and resulting from an opening gas pressure being applied on the opening leaf, with a value greater than or equal to a predetermined value and causing displacement of the opening leaf from the closed position to the open position after breakage of the mechanical fuse.

Abstract: A system for controlling at least one aircraft engine and an aircraft comprising such a control system are disclosed. The system (4) comprises a control lever (5), the intermediary range of automatic regulation thereof of the engine speed comprises a single marked position (II) with which there are associated a climbing speed and an automatic regulation speed. Such a lever is able to occupy another take-off and go-around marked position, with which there are associated a take-off speed and a go-around speed.

Abstract: A method for assembling a part of a metal material and a part of a composite material, the junction of the two parts being achieved through a fastener having a substantially constant section and received in a first hole formed in the part of a metal material and a second hole formed in the part of a composite material. According to the disclosed embodiments and before assembling the aforementioned parts, the method includes: an expansion step for generating a field of compression stresses at the periphery of the first hole and locally in the material constituting the part of a metal material using an expansion tool; a single boring step for making the first hole and the second hole with a diameter Øfinal substantially larger than the diameter of the fastener in order to leave a gap between the inner walls of the holes and the outer surface of the fastener; and an assembling step for placing the fastener inside the holes for maintaining together the metal part and the composite part.

Abstract: A target vertical speed, to be applied to the aircraft upon the initiation of the aircraft's flaring phase, is defined in relation to the ground. An optimized ground slope associated with an approach path to be tracked during the landing, is then determined as a function of the determined target vertical speed and of at least one outside parameter. This optimized ground slope is at least equal to a predefined ground slope. Upon interception by the aircraft with the approach path, the aircraft is guided to track the determined optimized ground slope associated with the approach path and reach the target vertical speed upon initiation of the flaring phase.

Abstract: The invention relates to an electronic module (2) comprising: an electronic card (4) on which electronic components (10) are disposed, two covers (6, 8), disposed on either side of the card (4). The cover (6) facing the components (10) has a central part (22) extending at a distance from the card (4) and a flanged edge (24) turned toward the card (4), prolonging one of the two opposite sides of the central part (22). This flanged edge (24) is prolonged by a flat support (26), extending in a plane parallel to the plane of the electronic card (4), the card (4) being added onto the said support (26). The covers (6, 8) bear indexing means (34), the electronic card (4) having indexing holes (36) cooperating with the indexing means (34) during positioning of the card (4) between the covers (6, 8).

Abstract: A Krueger, or leading edge flap, deployable from a lower aerodynamic surface of an aircraft main wing element so as to form a slot between the Krueger and the main wing element when deployed, the deployed Krueger having a leading edge, a trailing edge and upper and lower aerodynamic surfaces extending between the leading edge and the trailing edge, and a flow deflector which provides an effectively divergent flap profile thickness in the downstream direction at or adjacent the Krueger trailing edge so as to direct airflow away from the lower aerodynamic surface of the deployed Krueger towards an upper aerodynamic surface of the main wing element. Also, aircraft wing assembly including a main wing element and the Krueger.

Abstract: A monitoring device includes one or more devices for implementing monitoring, in order to check whether two flight management systems are able to operate in dual mode during operations requiring navigation and guidance performance. For example, a change condition verification device may be included in a second or slave flight management system so that sequencing requests and resynchronization requests received from a first or master flight management system are verified for accuracy before implementation. The verification may include comparison of positional data used by the first and second flight management systems or a comparison of a resynchronized flight plan to information from a navigation data database.

Abstract: A method for deactivating a steering system of a front landing gear of an aircraft, including detecting an activated status of the steering system, detecting a pilot control unit in neutral position, detecting towing conditions of the aircraft, detecting a rotational movement of the nose gear, and deactivating the steering system when operations to are verified. The disclosed embodiments also concern a system for implementing this method.

Abstract: The invention provides a method for manufacturing a monolithic torsion box inner structure (40) of an aircraft lifting surface comprising the following steps: a) providing a set of laminated preforms of a composite material for forming said torsion box inner structure (40), each laminated preform being configured for constituting a part of one component of the torsion box inner structure (40); b) arranging said laminated preforms in a curing tooling and subjecting the assembly to an autoclave cycle to co-cure said laminated preforms; c) demoulding the curing tooling in a vertical direction. The invention also provides an aircraft lifting surface wherein: the inner structure (40) of each torsion box (13) is manufactured by said method and the upper and lower skins (31, 33) are attached to the torsion box inner structure (40) with mechanical attachment means.

Abstract: A vacuum toilet unit having a urinal function with reduced noise emission, system design size and system weight, in which vacuum toilet unit a triggering device for triggering the vacuum valve is adapted in such a manner that the triggering unit may not be triggered when a sit-down toilet is in use as intended.

Abstract: A high lift system for an aircraft includes a basic body, a flap which is movably mounted on the basic body and has a flap edge, and a retaining element. The high lift system is set up to form a gap between the flap edge and the basic body. The retaining element is mounted on a region of the flap close to the flap edge and extends towards the basic body to restrict the distance between the flap edge and the basic body. The retaining element is preferably configured as a linear attachment means. Consequently, a gap dimension between a flap and a basic body can be influenced to restrict flexing effects during loading of the flap and of the basic body.

Abstract: A method of installing fuel system components in an aircraft wing is disclosed. An aircraft wing having a plurality of structural elements such as ribs which are joined together during assembly. The method includes the step of attaching at least some of the fuel system components to at least one of the structural elements prior to joining said structural elements together to assemble a wing. Also disclosed is a structural rib for an aircraft wing, configured to receive one or more fuel system components, and a combined structural rib and fuel system assembly.

Abstract: Structural component including at least one covering shell and a carrier structure, the covering shell designed in the form of a sandwich and formed by an inner skin section, an outer skin section and a shear-load absorbing core layer disposed between the two sections and connecting the inner and the outer skin sections to one another in a planar manner. The carrier structure is formed by at least one panel-shaped connecting part extending between and transversely to the inner and outer skin sections and connected along a reference longitudinal direction to the covering shell. The connecting part is located outside the carrier structure and fastened to the inner skin section resting thereon in a planar manner, wherein at least one profiled support extending along the reference longitudinal direction is provided in the covering shell in order to form a reinforcing section in the connecting region of the panel-shaped connecting part.

Abstract: A method for manufacturing a solid oxide fuel cell element by layer-wise buildup wherein at least one section of the element is built up by carrying out a step that at least includes the following at least once: applying a layer section of a particulate ceramic material with predefined dimensions onto a base layer in a predefined area and heating the layer section by means of a heat source such that the particles of the ceramic material connect to one another within the predefined dimensions. The solid oxide fuel cell element manufactured with the method is realized in one piece, as well as highly compact, and has a low weight.