Abstract: A load introducing element for a control surface of an aircraft or a spacecraft comprises at least one first component, one second component and one first flange. At least one surface area of the first component is adapted to conform to the inner contour of the control surface. The second component has at least one eye for receiving bearing means for mounting the control surface. A cross sectional profile of the first component has two or more essentially straight legs, which are connected together on their upper side by an upper edge which is adapted to an upper contour of the control surface. The load introducing element is formed by a fiber reinforced composite material having an integral type of construction in which all of the components are jointly infiltrated and cured. The invention also provides a method for producing such a load introducing element, a drive armature and an aircraft that includes such a load bearing element.

Abstract: The present invention concerns a composite plate (1) comprising a first cover layer (3), a second cover layer (5), and a core layer (7) arranged between the first and the second cover layers (3, 5) and having a plurality of cells (9) which are at least partially open towards the first cover layer (3) and which are separated from each other by walls as well as a method of draining such a composite plate (1). In order to provide such a composite plate (1) in which improved resistance to ingress of liquid or formation of liquid accumulations is guaranteed in a simple and continual fashion it is proposed that a draining layer (13) is provided in the first cover layer (3), wherein the cells (9) are at least partially covered by the draining layer (13).

Abstract: A method of transmitting data over a network, from a sending application to a receiving application, including: coding the data, by the sending application, by implementing a predefined rule; detecting alteration of at least one item of data transmitted, by the receiving application, by implementing the predefined rule; and in case an alteration of a data item is detected, restoring the altered data item. In the course of the coding, in the course of the alteration detection, and in the course of the restoration, a cyclic redundancy check or an encryption can be implemented.

Abstract: An aircraft nacelle includes at its outside wall a cowl moveable relative to the nacelle so as to block or unblock an opening. The cowl includes an articulation and locking/unlocking elements distant from the upstream edge of the cowl that include elements for limiting the appearance of scooping phenomena. The limiting elements include at least one lock integral with the rest of the nacelle or respectively the cowl that can occupy a locked state in which part of the lock interferes with the cowl or respectively the rest of the nacelle and prevents a deformation that includes a radial component of the cowl, and another free state in which the part no longer interferes with the cowl or respectively the rest of the nacelle and allows the opening movement of the cowl, with the switch from one state to the next being generated by a gas pressure variation.

Abstract: An apparatus is disclosed for monitoring the load on at least one part of an aircraft landing gear during landing of the aircraft. The apparatus comprises a housing containing a sensor which senses a parameter indicative of the load in the part of the landing gear, a processor which receives signals from the sensor and processes the signals to produce data representative of the parameter measured by the sensor, a battery which provides electrical power to the processor, a memory for storing measurement data from the processor, and a wireless transmitter which is controlled by the processor. The wireless transmitter is arranged to transmit at least some of the measurement data from the processor to a remote device located outside of the housing.

Abstract: An electrical power supply system and method for an aircraft. The system includes an electrical network including primary generators powering the electrical distribution channels, and an homopolar generator making it possible to create an artificial neutral.

Abstract: An acoustic treatment panel that is connected to an air intake of an aircraft nacelle, includes at least one acoustically resistive structure (30) and a reflective layer (32), between which are located—in a direction that is essentially perpendicular to the longitudinal direction of the nacelle—bands (34) of alveolar cells spaced in such a way as to allow the passage of hot air provided for a frost treatment, characterized in that it includes pipes (36) for hot air that are each delimited by at least one partition that extends from the acoustically resistive layer (30) up to the reflective layer (32) in such a way as to insulate the bands (34) of cells in the longitudinal direction.

Abstract: A monitoring device for automatically monitoring the ability of an aircraft to follow a flight trajectory with at least one turn includes a series of elements that estimate the ability of the aircraft to follow at least one turn of the flight trajectory. For example, a turn radius and limit speed for each of the upcoming turns in a flight plan (or a partial portion of the upcoming turns) are analyzed by comparing to a current speed of the aircraft to determine if there will be any risk of excursion outside the flight plan path, such that warnings can be emitted to a crew of the aircraft to take corrective action before the turns are performed. Consequently, required navigational performance maneuvers can be assured before the beginning of the turns in the flight plan.

Abstract: A standardized identification code is used to identify each flight parameter used on board an aircraft and to provide some of its characteristic information. Descriptive complementary information is advantageously associated with the identification codes to form parameter identification maps stored, for example, in a shared database. The parameter identification codes may in particular be used to perform certain checks when parameter values are received. These checks make it possible to process only the monitored parameter values and to generate alerts if an inconsistency is detected.

Abstract: An electronic circuit, and a system including such a circuit, for determining a datum representative of a parameter of air surrounding an aircraft, including: a mechanism receiving, from a plurality of sources, a plurality of respective measurement data representative of a measured value of the parameter; a mechanism determining the datum representative of the parameter based on the measurement data; and a mechanism transmitting the datum representative of the parameter to a computer associated with an aircraft engine.

Abstract: An aircraft wing box spanwise joint, comprising a rib having a web, and a pair of rib fittings joined together, each rib fitting forming a closed loop around the periphery of the rib, wherein the rib is integrally formed with one of the rib fittings. Also, an aircraft wing including two or more of the joints. Also, a method of forming an aircraft wing box spanwise joint, the method comprising forming a pair of rib fittings, wherein one of the rib fittings is integrally formed with a rib having a web, each rib fitting forming a closed loop around the periphery of the rib, bringing the rib fittings together, and joining the rib fittings together.

Abstract: A sealing member for forming a seal in an aircraft, the sealing member comprising: a sealing material; and a stiffening element which provides structural support to the sealing material and comprises a material with a glass transition temperature below +50° C. The stiffening element is relatively flexible when the aircraft is at low altitude (high temperature) but becomes relatively stiff (increasing resistance to seal flutter) when the aircraft is at cruise altitude (low temperature).

Abstract: A fairing device for creating an aerodynamic cover for an area of an aircraft structure, including a first fairing part with an outer side forming a first exterior flow contour, and having a fairing section for contacting a first section of the aircraft structure and a connecting section. The first fairing part includes a mounting device for receiving a connecting element. The fairing device includes a second fairing part including a fairing section having an outer side forming a second exterior flow contour and is designed for contacting a second section of the aircraft structure and a connecting section. The shape of the outer side of the second fairing part is adapted to the inner side of the connecting section of the first fairing part in an overlapping area, so the connecting section of the first fairing part forms a joint piece protruding over the second fairing part in the overlapping area.

Abstract: Computer-assisted method for optimizing surfaces of composite-material structures as part of a design process that includes the following stages: a) Providing a multi-cell surface (11) of the structure obtained using aerodynamic calculations; b) Transforming said multi-cell surface (11) into an optimized surface (13) with fewer cells, concatenating contiguous cells and maintaining point and tangent continuity between them; c) Using said optimized surface (13) as geometric master when designing the components of the structure. The method is particularly applicable to the design of structures with a plurality of components and in particular fuselages of aircraft made of composite material. The invention also relates to a computer program for performing the method.

Abstract: According to the invention, at least one of the counterweights (40, 40.1, 40.2, 40.3, 40.4) is mobile mounted on a guiding slot (24, 34) coaxial to the hub envelope (22, 32) that surrounds the hub (21, 31) of the corresponding propeller (2, 3), the movement of said mobile counterweight (40, 40.1, 40.2, 40., 40.4) along said guiding slot (24, 34) being controlled on the basis of an estimation of the possible unbalance of said propulsive system (1).

Abstract: A method for the friction stir welding of two components, in particular of two shell components of a fuselage structure of an aircraft and spacecraft, said method comprising the following method steps: positioning the two components relative to one another in such a way that a connection region is formed between the two components; friction stir welding the two components by means of a friction stir welding tool which penetrates the connection region in order to produce a weld which permeates the connection region with the formation of an unpenetrated weld edge portion of the connection region; and introducing internal compressive stresses, at least in the weld edge portion of the connection region. Further a device for the friction stir welding of two components, in particular of two shell components of a fuselage structure of an aircraft and spacecraft is provided.

Abstract: A method and a device are disclosed for concentration of messages transmitted by at least two separate transmitters in a communication network to which there are connected these transmitters and an addressee of the data contained in the messages. After receiving the messages to be concentrated, the data contained in these messages are extracted. A concentration frame comprising the extracted data and at least one information item making it possible to identify the addressee is then constructed and transmitted The size of the concentration message is smaller than the maximum size of the data packets exchanged in the communication network.

Abstract: A process for manufacturing a curved part of composite material, during which the layers of fibers of composite materials that will compose the part are held taut at least during the bending step, and displacement of the layers with relation to each other is controlled, is disclosed. A device capable of implementing this type of processs is also disclosed.

Abstract: A supply system is provided that includes, but is not limited to a profile element. The profile element includes, but is not limited to a front wall, a rear wall, and webs between the front wall and the rear wall so that there are ducts within the profile element. The supply system also includes, but is not limited to at least one functional component integrated in at least one of the plurality of ducts.