Abstract: A system and method for selecting a datum representative of an air parameter, including a plurality of sources each capable of delivering a datum representative of a measured value of the parameter. The system includes: a mechanism for determining, for at least some sources, a number of other sources from the plurality of sources in agreement with a source in question; and a mechanism for selecting the datum selected from the data delivered by the sources for which the determined agreement number is the maximum. An engine control system, or an aircraft can include such a system or implement such a method.

Abstract: The present invention provides a device for mounting systems, for example an electrical or fluid-conveying line, on a structure, in particular of an aircraft or spacecraft, the device comprising a basic holder which is fastenable to the structure and a system holder for mounting the systems, the system holder being fastenable to a first interface of the basic holder, which system holder is fastenable to a first interface of the basic holder; the basic holder comprising a first part, which comprises the first interface, and a second part, one end of which is attachable to the first part so as to be pivotal about a pivot axis and the other end of which is fastenable to the structure.

Abstract: A repair part enables rapid and efficient repair of damaged metal structures, in particular airframe fuselage skins having internal and external faces, without necessitating any additional thickness compromising the transmission of waves. To this end, the repair part includes a double internal/external plate adapted to be fastened to the internal face and the external face of the metal structure, respectively. The repair part also includes a central hub connecting the internal plate and the external plate and forming a groove between the plates. The part is constituted of a single composite material block, and a glass ply, lining the groove, may be positioned between the plates and the structure. The hub may have passing through it at least one orifice adapted to allow connections to pass through the structure.

Abstract: A process for the production of an acoustic treatment panel that can be connected at a surface of an aircraft, in particular at a leading edge such as an air intake of an aircraft nacelle, whereby the panel includes an acoustically resistive layer (24), at least one alveolar structure (26), and a reflective layer (28), and channels (30) placed between the alveolar structure and the acoustically resistive layer, each channel being bordered by a wall (32), the process including deforming a layer so as to produce furrows at one of its surfaces, flattening and making integral the deformed layer (34) with the acoustically resistive layer so as to border the channels, and removing material in such a way as to eliminate at least a portion of the thickness of the deformed layer (34) in which the furrows are formed between the channels, prior to the assembly of the alveolar structure.

Abstract: A remote data concentrator (RDC) for an avionics network, the RDC comprising an input/output interface (I/O) for connection to one or more input/output devices, and a network interface for connection to a remote processor, wherein the RDC is operable to provide communication between the input/output device(s) and the remote processor, and wherein the RDC further comprises a set of instructions for autonomously driving an output device connected to the I/O. Also, an avionics network including the RDC; an aircraft including the RDC; and a method of operating the RDC.

Abstract: A method and a device are disclosed for exchanging data between a technical management system of an aircraft and a mission management system of the aircraft, in order to permit one of the systems to determine the consequences of an event detected in the other of the systems. After at least one event has been detected in one of the technical management and mission management systems of the aircraft, at least one information item pertaining to the detected event is transmitted to the other of the technical management and mission management systems of the aircraft. The consequences of the event detected in the other of the technical management and mission management systems of the aircraft are then determined. The adaptation of at least one datum of the other of the technical management and mission management systems of the aircraft is evaluated in response to the determination.

Abstract: A fiber laying machine includes a laying head with a roller able to pivot about an axis of rotation and to apply a plurality of preimpregnated fibers to an application surface by rolling over the application surface. The fibers are distributed along a lower generatrix of the roller and in contact with an exterior surface of the roller over an angle of wrap. The roller includes a cylindrical body, pivoting rings around the body, and means for immobilizing the pivoting rings with respect to the body in a direction parallel to the axis of rotation. The pivoting rings are able to pivot independently of one another.

Abstract: Rear fuselage of an aircraft comprising a tail cone end and a rest of the real fuselage whereby the tail cone end is attached to the rest of the rear fuselage by means of an attachment system comprising two upper lugs, two lower lugs and a detachable balancer fitting. The balancer fitting is an adjustable fitting, being locked in a Z and Y directions of a Cartesian axis and being movable along an X direction of the Cartesian axis providing guidance for the tail cone end and the rest of the rear fuselage.

Abstract: A wing-fuselage connection of an aircraft, in which a wing (2) that is arranged in the upper region of the fuselage (1) is connected to the fuselage (1) by means of a number of couplings (3, 4, 5, 6), wherein the couplings (3, 4, 5, 6) are provided for taking up forces in various directions and are designed for a maximum load carrying capacity, in particular for a nominal flight- and landing load (10) or a nominal crash load. According to the invention, the load carrying capacity of the individual wing couplings (3, 4, 5, 6) and their direction of force take-up are matched to each other such that in the case of a defect in one of the couplings (3, 4, 5, 6) the maximum load carrying capacity of the remaining couplings (3, 4, 5, 6) is adequate for safe normal flight operation.

Abstract: A fluid ejection device for example used as a fire extinguisher in which ejected fluid is an extinguishing agent in liquid or powdery form. The device includes: a cylinder shaped tank, split hermetically, perpendicular to its axis, into two chambers by a piston, slidable axially inside the tank; a first chamber, including a non-gaseous fluid, which communicates with an ejection port closed by a cap, which can open for a pressure greater than or equal to a defined pressure in the first chamber; a second pressurization chamber to be connected to a mechanism increasing pressure in the chamber; and a mechanism to link the piston to the tank in full fixity at a storage position, which mechanism can break and release the piston for axial translation at a pressure higher than or equal to a given pressure in the pressurization chamber, to cause the fluid to be ejected.

Abstract: A cabin structural segment is provided for an aircraft that includes, but is not limited to a fuselage structure and a floor structure. The fuselage structure defines an interior and separating it from an environment. The fuselage structure includes, but is not limited to an opening for a door. It is possible to provide via the opening a connection between the interior and the environment. The cabin structural segment is designed to be self-supporting. The cabin structural segment is fastenable exclusively to the floor structure. The cabin structural segment is constructed in such a way that the one cabin structural segment frames the opening.

Abstract: A diagnostic system of an aircraft, comprising a plurality of sub-systems at least one of which performs monitoring and notification of at least one detected event, using graphs of feared events. After a message of notification of occurrence of the detected event has been received, a set of feared events linked to this message is created from the graph of feared events, and logic expressions are constructed according to logic links represented in the graph of feared events. A group of feared events then is created according to elements of the logic expressions. The minimal vertexes of the logic expressions associated with the feared events of the group are calculated and form a diagnosis of the system.

Abstract: A pressurized fuselage of an aircraft includes a fuselage structure and a pressure bulkhead mounted therein for forming a fuselage-internal pressure region. The pressure bulkhead is attached on the edge region, by way of mounting means, to the inside of the fuselage structure. The mounting means comprise at least one pivoting socket arrangement, arranged on the edge side of the pressure bulkhead, which edge side faces away from the pressure region, and interacts with the fuselage structure, as well as a supporting frame element, arranged on the opposite edge side and supporting itself on the fuselage structure.

Abstract: A method for the assembly of an aircraft fuselage, to a fuselage manufacturing station and to a construction kit includes providing a pre-assembled cockpit unit, a pre-assembled wing box, a pre-assembled tail unit and a plurality of pre-fabricated fuselage shell segments. Furthermore, the method involves positioning the cockpit unit, the wing box and the tail unit. Moreover, a first front fuselage shell segment is positioned on a front connecting region of the wing box, and a first rear fuselage shell segment is positioned on a rear connecting region of the wing box. The first front fuselage shell segment is joined to a second front fuselage shell segment, and the first rear fuselage shell segment is joined to a second rear fuselage shell segment. As a result of the above, following the assembly of the aircraft fuselage an aircraft fuselage can be provided that already comprises equipment elements or functional elements.

Abstract: The present invention provides a flat speaker, in particular in the aerospace sector, with a panel for generating acoustic signals by vibration of the same, and a vibration exciter which is connected to a panel and excites this to vibrate. Here the panel has an edge stiffening. This provides the panel with the required stiffness, particularly against hand pressures, but at the same it guarantees high energy efficiency of the flat speaker.

Abstract: The subject of the invention is a control unit (A), which comprises actuation units (F) such as a rudder and brakes for a pilot in an aircraft, which comprises a rotating shaft (2) mobile in rotation around an axis (40); said shaft is driven in rotation when the pilot performs an action on the actuation units (F), in particular the brake pedals, by mechanical transmission between said shaft and said actuation units, and which comprises a device for generating resistive torque (1) designed to be fastened along the rotating axis of the control unit; the device for generating resistive torque comprises a friction disk (3, 4, 5) mounted axially and fastened to the rotating axle (2), a first annular track (6, 7, 8) fastened to a frame element (9) of the control unit; and means of support (10, 11, 12).

Abstract: A clamp block assembly for securing hydraulic pipes, the clamp block assembly comprising one or more unitary clamp blocks of deformable material each having a through hole for receiving a respective pipe, and a clamp adapted to apply a predetermined load around the clamp block(s).

Abstract: Flat illuminating display device with light emitting means to illuminate a film for display of an image applied to a display area, wherein the light emitting means are embodied as at least one light coupling unit arranged laterally at a translucent film thus forming a light duct, wherein the light such fed into the adjacent edge area into the film is reflected by a reflective layer, which is applied on at least one side, to homogeneously spread within the film, wherein a reflection screen to obtain a light emission is provided opposite of the display area to create said display area.

Abstract: The invention provides an aircraft landing gear arrangement, comprising a bogie including a steerable axle pivotally mounted to said bogie. A locking mechanism is provided to lock the steerable axle in the straight ahead position, where the locking mechanism includes an over-center linkage arrangement.

Abstract: A process for manufacturing a stiffener made of composite material with an inside surface of a concave shape, includes producing a flat strip (18) that includes at least one layer of fibers; heating it to be able to deform it; connecting one of the lateral edges of the strip (18) to a rotary mandrel (36) in such a way as to cause a winding of the strip on the mandrel (36) during its rotation, whereby the mandrel (36) has an outside surface (46) of which at least one part corresponds to the inside surface of the stiffener to be produced; and exerting tension at the other lateral edge of the strip (18) in a direction that is opposite to the direction of the movement of the strip (18) caused by the winding on the rotary mandrel (36).