Abstract: A device includes means for generating and applying to an aircraft protecting orders avoiding a flight with an excessive descent rate. More specifically, the device includes components configured to perform a series of operations including measuring the current vertical speed and the current height of the aircraft and comparing these flight parameters with a safety envelope defining couples of vertical speed and height that are indicative of an excessive descent rate. If the current vertical speed and height are located in the safety envelope, a protection is triggered by generating protecting orders to remove the aircraft from the safety envelope and applying those protecting orders to control surfaces of the aircraft.

Abstract: A cabin equipment component connection system for an aircraft comprises a plurality of connecting elements, which are adapted to be connected to a cabin equipment component in order to connect the cabin equipment component to a higher-level system of the aircraft. In at least one zone of the cabin equipment component connection system, a number and an arrangement of the connecting elements in the cabin of the aircraft are selected such that cabin equipment components that are provided in a first number and/or a first arrangement in the cabin of the aircraft are connectable to the connecting elements of the cabin equipment component connection system, and that cabin equipment components that are provided in a second number and/or a second arrangement in the cabin of the aircraft are connectable to the connecting elements of the cabin equipment component connection system.

Abstract: A ceiling panel is configured for attaching a curtain in a cabin of a transportation device with an attachment unit, a mounting unit, and a curtain attachment unit. The ceiling panel is configured to integrate the attachment unit, the attachment unit is configured to attach the mounting unit to the ceiling panel, the mounting unit is configured to attach the curtain attachment unit, and the curtain attachment unit is configured to support the curtain.

Abstract: Pultrusion methods and apparatus for manufacturing a profiled preform or FRP-component with cross-sectional segments that extend angularly to one another from a plurality of semifinished products in a quasi-continuous process, where: at least one multilayer semifinished product arrangement [of a multilayer semifinished product arrangement] is dispensed from a dispenser unit in order to manufacture the preform, with the multilayer semifinished product arrangement dispensed from the dispenser unit being fed to the forming device and including a combination of several webs of semifinished reinforcement fiber layers and at least one resin film; the semifinished product arrangement is guided through a forming device and at least one cross-sectional segment of the semifinished product arrangement is angled in order to form an angle profile, with the semifinished product arrangement being compressed in a pressing device, optionally after a hardening process, and with a longitudinal section of the preform or the comp

Abstract: A cladding apparatus is provided for the interior of an aircraft that includes, but is not limited to at least one two-dimensional fabric sheet, at least one guide device, and at least one tensioning element. The guide device is configured to be attached in the interior along a direction of extension of the interior, and slidably guide the fabric sheet at least in a first section of the interior along the direction of extension. The tensioning element is, furthermore, configured to be attached in the interior, and by producing a tensile force that acts on the front edge and/or the rear edge of the fabric sheet to stretch taut the fabric sheet along the direction of extension of the interior.

Abstract: The method of the invention comprises imparting to the flaps (6G, 6D) of said aircraft either a nose-up deflection (?F) corresponding to the maximum sharpness if the nose-up order is higher than a predetermined threshold, or a deflection (?0) corresponding to the minimum drag if the nose-up order is lower than said threshold.

Abstract: A fire fighting system for extinguishing a fire, which has a fuel cell for producing a nitrogen-enriched cathode exhaust air. The fuel cell is supplied with air and a fuel. Within the fuel cell, the air is then reduced to a determined oxygen content. The exhaust air is supplied to the fire source.

Abstract: In the method of accessing an information system of an aircraft the system receives an authenticator request from a connector of the aircraft; the system determines whether the connector presents a predetermined characteristic; and in the event that the system determines that the connector does indeed present the predetermined characteristic, the system sends an authenticator to the connector. Provision is also made for: the system receives an authenticator the system determines whether the authenticator is valid; and in the event that the system determines that the authenticator is indeed valid, the system authorizes access to the system from a connector of the aircraft from which the authenticator was sent.

Abstract: A detection device determines whether an uncontrolled movement of a control surface of an aircraft is occurring. The device includes means for calculating the difference between a theoretical command and an actual command in order to form a residual value, and means for detecting an uncontrolled movement of the control surface, if a comparison value depending on this residual value is greater than a threshold value If the comparison value is greater than the threshold value during a confirmation time, then the uncontrolled movement of the control surface of the aircraft is confirmed.

Abstract: A pylon for attaching a turbine engine of an aircraft having a rigid structure including protruding fittings each having a first orifice and a plurality of ties to attach the pylon onto a wing of the aircraft, the plurality of ties comprising two side front ties to take the thrust forces, the two side front being secured to the first orifices of the protruding fittings to attach the rigid structure firmly to the wing. The plurality of ties further comprises a center front tie positioned between the two side front ties, the center front tie including a ball joint to take forces in a lateral direction of the rigid structure.

Abstract: The invention relates to a radome (1) for an aircraft, and more specifically to a device for connecting said radome to the structure of said aircraft. The radome that is the subject of the invention comprises a plurality of locking units able to bring together the opposing surfaces of the aircraft's fuselage (10) and the radome (1), each unit comprising: locking means (20) able to exercise a traction force on the surface of the fuselage, substantially normal to the surface, via attachment means; centering means able to withstand the shear forces substantially tangential to the opposing surfaces of the fuselage and radome; the locking means (20) are placed such that they are located inside the cone of resulting forces on the centering means so as to minimize the bending stresses generated by the assembly in the radome (1).

Abstract: The dialog device includes a display screen, on which are displayed three graphic representations, which are respectively associated with the three control axes of the aircraft, each of said graphic representations comprising a plurality of portions, each of which is associated with a guidance mode of the associated control axis, so that all the possible guidance modes of the guidance system are thus represented, this representation highlighting the fact that the guidance modes are active exclusively on a given guidance axis.

Abstract: A locking apparatus for an object that is lockable on a rail is provided such that the object may be undone in a single manual operating step. The apparatus may be used in a passenger aircraft in which it is necessary to slide seats or other built-in devices. The apparatus includes at least one first base body, at least one first locking body, and at least one first operating element. The at least one first base body is designed to be placed on top of the rail. The at least one first locking body is movably held to the at least one first base body, and is shaped to be placed into the rail. The at least one first operating element is connected to the at least one first locking body for moving the at least one first locking body in the direction of the interior of the rail.

Abstract: An aircraft wing comprising a main wing element with a spar and a leading edge rib which is supported by the spar and extends forward of the spar; a high lift device which is movably mounted to the main wing element; and an actuation mechanism comprising a drive shaft and a gear train. The gear train comprising a drive cog which is carried by the drive shaft, an actuator cog which is coupled to the high lift device, and one or more intermediate cogs which are mounted to the rib and coupled in series with the drive cog and the actuator cog so as to transmit torque from the drive cog to the actuator cog which moves the high lift device between a retracted position and an extended position in which the high lift device increases the camber of the wing. The sizes of the cogs in the gear train are selected so that the drive shaft rotates at a higher rate than the high lift device.

Abstract: An apparatus for fabricating a fibre reinforced thermoplastic composite structure is described. The apparatus comprises a localised heat source arranged to heat a portion of a stack of fibre reinforced thermoplastic material layers and an ultrasonic transducer arranged to locally introduce ultrasonic energy waves to the heated portion of the fibre reinforced thermoplastic material layers. The apparatus makes it possible to achieve ultrasonic consolidation of the layers occurs.

Abstract: A system for detecting jamming and/or uncontrolled movement of an aircraft control surface includes first means for estimating the value of at least one parameter of an equation simulating the feedback loop dynamic of the control surface, according to a recursive autoregressive method with exogenous variable of RARX type in a recursive least squares way, and second means for detecting jamming and/or uncontrolled movement of the control surface, according to the estimated parameter value by the application of a decision test in the parametric space.

Abstract: A non-destructive determination of material characteristics of an aircraft component is provided. To provide a simple determination of material characteristics, which can be implemented economically, it is provided to make available image data of a layer, which can be detected from outside using electromagnetic radiation, of a workpiece to be examined; to detect first areas having a first pixel characteristic using the image data; and to detect second areas having a second pixel characteristic using the image data; the first pixel characteristic being associated with a fiber inlay of a fiber composite layer; and the second pixel characteristic being associated with an at least part-crystalline thermoplastic polymer of the fiber composite layer, which thermoplastic polymer is in a crystalline state; and to determine a relationship of the first areas to the second areas.

Abstract: The invention relates to a method for joining cured stringers to at least one structural component of an aircraft or spacecraft, including placing the stringers onto the at least one structural component, depositing and pressing respective vacuum film strips such that each strip is attached to a pair of stringers and present between the pair of stringers with the use of vacuum sealing means in such a manner that a continuous vacuum arrangement, comprising the covering vacuum films and the vacuum film strips, is formed, and pressurized joining of the stringers to the at least one structural component by means of the continuous vacuum arrangement formed.

Abstract: An integration method and module aims at simplifying the electrical connections between equipment and an electrical power center to be supplied electricity, while enabling a good accessibility of each piece of equipment for easier maintenance. To do so, a particular integration of this equipment is carried out so as to be able to connect the equipment in a direct extension of the electrical power center. According to one embodiment, an integration module includes a frame and a cover, the frame having a substantially parallelepipedic shape adapted to be able to extend longitudinally along a main axis in parallel with a longitudinal main side of the electrical power center. Cells, which define a constant cross section and an adjustable width enabled by movable intermediary walls, extend perpendicularly to the main longitudinal axis. Such cells are adapted to receive formatted electrical equipment.

Abstract: An engine simulator for wind tunnel models exhibits a turbine with an inlet for a pressurized fluid and an outlet for a relieved fluid, a flow-type body arranged downstream from the turbine, a jacket that at least partially envelops the flow-type body with the formation of a gap, and at least two electrodes. A downstream end of the flow-type body is provided with a heater coating comprised of a matrix material that contains a conductivity additive and is connected with the electrodes for applying an electrical voltage. This may make it possible to prevent ice formation on the trailing edge of the flow-type body.