Abstract: The invention relates to a method for manufacturing flat, single or double curved core composites 1, 23 with at least one folded honeycomb core 4, 19. Prior to applying the initially not yet hardened cover layers 2, 3, 13, 22 a curable and later removable core filler material 15, 16 is introduced into full-length drainage-enabling channels 5, 6 of the folded honeycomb core 4, 19 in order to prevent telegraphing of the cover layers 2, 3, 13, 22 into the channels 5, 6 of the folded honeycomb core when arranging and/or hardening the cover layers 2, 3, 13, 22 and to produce edge-free and polygon-free surfaces of the core composite 1, 23. The core composites 1, 23 made according to the method have optimum structural mechanical properties, an ideal surface quality from the aerodynamic and aesthetic point of view, whereby a direct reprocessing of the core composites 1, 23 is possible without the need for further time and cost-intensive as well as in some circumstances weight-increasing finishing steps.

Abstract: A device for producing a composite material part designed to be in contact with aerodynamic flows, in particular a portion of the fuselage, whereby the device includes at least one mold (32), elements (34, 36, 38) for compressing the part that is to be produced, as well as a system for drainage of the gases emanating from the part that is to be produced that includes at least one plate (42), characterized in that the at least one plate (42) includes a number of openings (44) whose shapes and/or arrangement limit the degradation of the aerodynamic characteristics of the part that is to be produced.

Abstract: A transverse splicing plate for producing a fuselage of an aircraft by connecting several CFP fuselage sections that have in particular been produced in the winding method, in each case by forming a transverse seam, wherein the flexible transverse splicing plate is of a multilayer construction, in other words it comprises a multitude of plate segments arranged one above the other, wherein each of the plate segments comprises a multitude of longitudinal slits, each being able independently of each other to make small radial bending movements in order to cause tolerance compensation in radial direction between the fuselage sections to be joined, in which tolerance compensation a sliding movement between the sub-plates of the plate segments arranged one above the other takes place in axial direction of the barrel-shaped fuselage sections, and wherein on the inside the ends of the fuselage sections comprise chamfers; as well as a method for producing a connection between two CFP fuselage sections, which have pref

Abstract: A mounting device for aircraft supply systems comprises a cross member and at least one support module including a body having a shape complementary to that of a cross member. The body includes a structure for securing an aircraft supply system, an opening, and a pin, wherein the opening forms a guide that is able to receive a portion of the pin. The cross member includes grooves that are regularly spaced apart in the direction of elongation of said cross member. The pin has a shape complementary to that of the grooves and has a lip transverse to the direction of elongation of the pin. The support module is anchored to the cross member by the pin being inserted into the opening, the pin engaging with one of the grooves, as far as an anchoring position in which the lip is in contact with the support module.

Abstract: The present invention provides a fireproof bulkhead, having a highly porous structure with an intumescent coating, the highly porous structure being formed as a reticulated foam or as a highly porous pimple or nub structure.

Abstract: There is provided an aerofoil comprising an inboard section, a tip section moveable between a flying configuration and a parked configuration, a hinge shaft mounted at a compound angle in the inboard section, a fixed gear mounted concentrically on the hinge shaft and a drive gear coupled to the tip section and configured to mesh with the fixed gear, wherein a rotation of the drive gear against the fixed gear causes the tip section to rotate about the hinge shaft between the flying configuration and the parked configuration.

Abstract: A reinforcement structure for an opening in the primary structure of an aircraft, the structure comprising a skin, frame members which are transverse with respect to the flying direction of the aircraft, and stringers which are longitudinal with respect to the flying direction of the aircraft. The reinforcing structure includes a perimetral reinforcing element situated along the edge of the opening and reproducing the geometrical form thereof; at least one pair of transverse reinforcing elements arranged on both transverse sides of the opening; and at least one pair of longitudinal reinforcing elements arranged on both longitudinal sides of the opening.

Abstract: The device includes elements of a processing unit which determine a limit trajectory representing a flight trajectory which is compatible with the aircraft performance during the approach and which shows the limits for the flight of the aircraft. For example, a vertical profile and a horizontal trajectory are determined, with the horizontal trajectory being non-linear so that the energy of the aircraft can be sufficiently dissipated before final approach along an approach axis, while also avoiding obstacles. Thus, a flight trajectory is determined even when the aircraft has deviated from a flight plan and approach axis.

Abstract: An aircraft fuel system has a fuel tank with first and second cells separated by one or more baffles. A venting system reduces pressure difference between the interior and exterior of the fuel tank, and an inerting system supplies oxygen-depleted gas to the fuel tank. The baffles permit the flow of fluid between the cells. The venting system has one or more vent nozzles within the fuel tank and in fluid communication with one or more vent ports. The inerting system has one or more inerting nozzles for injecting oxygen-depleted gas into the first and second cells. A control device varies the ratio between the total flow rates of the oxygen-depleted gas into the first and second cells.

Abstract: The aircraft includes a structural portion such as a fuselage, a wing, or a tail, the structural portion including a wall separating the inside from the outside of the portion and including fractions defining between them an inside volume of the portion and at least one structural partition separating zones of the volume, e.g. a front zone and a rear zone, from each other, the partition including at least one flexible diaphragm suitable for deforming and at least two preferably rigid supports supporting the diaphragm in discontinuous manner.

Abstract: The invention in particular has as an object the incremental configuration of an IMA-type module, the module comprising temporal and hardware resources as well as an operating system allowing a segregated running of at least two applications with the aid of at least one part of the resources. After having obtained (305) at least one first configuration parameter of at least one part of the resources, this parameter applying to a resource specific to the operating system or a resource common to the operating system and to at least one of the applications or to the applications, the module is configured (310) according to this parameter. A second configuration parameter of at least one part of the resources then is obtained (320), this second parameter applying to a resource specific to one of the applications. The module then is configured (330) according to the said at least one second parameter.

Abstract: The present invention relates to a method of monitoring the condition of structural components, in which an optical sensor in conjunction with a computing unit ascertains image deviations from successive images of the structural components to be monitored, and therefrom ascertains changes in shape of the structure. Robust three-dimensional scanning of the structural components is possible when using two or more sensors. The invention further relates to an apparatus for monitoring the condition of structural components having an optical sensor and an apparatus having two or more sensors. Finally the invention relates to an aircraft in which the methods or apparatuses according to the invention are used.

Abstract: A connecting rod for the structural reinforcement of a fuselage structure of an aircraft includes a shank and eyes arranged at the shank ends on both sides for connecting the connecting rod to the fuselage structure. The connecting rod may have a reinforcing arrangement, which is configured as an all-over casing, the casing being formed by mechanically high-strength reinforcing fibers. The casing may also be formed by reinforcing fiber strands, which for their part can include a multiplicity of discrete reinforcing fibers running parallel to one another. Carbon fibers, glass fibers, aramid fibers and high-strength ceramic fibers come into consideration in particular as reinforcing fibers.

Abstract: The invention relates to a method for fastening an element of airplane interior equipment to a supporting structure in an airplane, comprising the steps of connecting the element of the airplane interior equipment to a first fixing device by using a first locking device, pivoting the element of the airplane interior equipment relative to the supporting structure, and connecting the element of the airplane interior equipment to a second fixing device by using a second locking device. Thus the element of the airplane interior equipment is fastened relative to the supporting structure.

Abstract: A method for producing an integral reinforced fiber composite component comprising at least one hollow fiber reinforcing component and a shell component is disclosed and can include first providing a mold core having a target cross-section deviating from a round cross-section adaptable to an inner cross-section of the hollow reinforcing component, introducing the mold core into a cavity of the hollow reinforcing component and fixing it thereafter in the cavity with a fixing agent applying the hollow reinforcing component with the mold core fixed therein to the shell component, and subjecting the mold core to a pressurized medium while applying heat and/or pressure to this arrangement to produce the integral reinforced fiber composite component.

Abstract: A device and method for assembling two structural elements made from a composite material is provided. The device includes two cylindrical flanged receptacles, each pierced by an aperture perpendicular to the axis of the cylinder, and a shaft that can be introduced into said apertures. The device also includes bearing means, which bear on the interior surfaces of the cylindrical receptacles and can maintain tension in the shaft when the shaft extends through the apertures in the two receptacles. The device includes means of placing the shaft under tension.

Abstract: An aircraft pressure bulkhead electrical connector comprising a first connection terminal proximate at least one side of the electrical connector and a pressure seal arranged to maintain an applied air pressure differential across the electrical connector in use.

Abstract: To produce an insulated current sensor for slaving power devices in the field of avionics, use is made of a magnetic core through which there passes an element traversed by a current to be measured. The magnetic core comprises a secondary winding across the terminals of which are connected an oscillator and a measurement device. The cooperation of the oscillator and of the measurement device makes it possible to circumvent all the traditional drifting of current sensors.

Abstract: A silencer for an auxiliary power unit of an aircraft includes an inlet, an outlet, a housing, and a flow channel of a porous material, arranged in the housing. Between the housing and the flow channel an intermediate space is created, which space is divided by at least one outer partition into outer cells arranged around the flow channel. A central body includes a casing that is permeable to gas at least in some regions and that is arranged in the interior of the silencer. The central body includes inner partitions dividing the central body into inner cells. The resonance frequency of the inner cells corresponds to the natural frequency of the first radial mode in a channel formed between the central body and the inner surface of the inlet. In this manner particularly good sound attenuation is achieved with a compact installation space of a silencer.

Abstract: An anti-collision aircraft light comprises at least one LED and a control unit for operating the at least one LED in a pulsed manner. In this anti-collision aircraft light, the control unit comprises an ambient temperature sensor for sensing the ambient temperature and an adjustable current control for setting an LED operating current depending on the sensed ambient temperature. The control unit further includes a light intensity sensor for sensing the intensity of the light emitted from the at least one LED, an integrator connected to the light sensor for integrating the sensed light intensity, and a comparator for comparing the integrated light intensity to a threshold value. The operating current for the at least one LED is interrupted as soon as the integrated light intensity is equal to the threshold value.