Abstract: An acoustic treatment structure related to a leading edge onto which an aerodynamic stream flows, in particular at an air intake of an aircraft nacelle, includes—from the outside to the inside—at least one acoustically resistive substructure (30), at least one alveolar substructure including strips (32) of cells, arranged in a direction that is essentially perpendicular to the direction of flow of the aerodynamic stream, and at least one reflective layer (34). Each strip (32) includes a first part that insulates the strips from one another, called a support, with a U-shaped cross-section in the longitudinal direction, whose open surface that is opposite to the bottom of the U shape is flattened against the acoustically resistive substructure (30), and at least a second part, called partitioning, making it possible to partition the space that is delimited by the support and the acoustically resistive substructure (30) into cells.

Abstract: The present invention relates to a method for detecting a defective sandwich component, particularly in aircraft construction, the method comprising the following steps: forming at least one measuring chamber in a core arrangement of a sandwich component, said at least one measuring chamber having an outwardly open end; subjecting the at least one measuring chamber to a predetermined pressure; and detecting and evaluating the pressure forming in the at least one measuring chamber.

Abstract: A method of managing an electrical power supply outage on board an aircraft, including the following operations: —detection of an electrical power supply outage, —measurement of a duration of the power supply outage by measuring a discharge time of a capacitor and comparing this measured duration with a threshold duration, —saving a long outage indication when the duration of the outage is greater than a threshold duration. The disclosed embodiments also relates to a system implementing this method and including: —a circuit for detecting an electrical power supply outage, —a circuit for measuring a duration of the power supply outage, and—a circuit for managing indications able to manage emissions of signals according to the measured duration of the power supply outage.

Abstract: The invention concerns a sensor simulation system. The simulation system (1) comprises a generator (3) that generates a digital signal by direct digital frequency synthesis, based on the following parameters: a frequency, an amplitude, a phase and amplitude shift; a digital/analog converter (4), and a means (6) that modulates the signal received from said converter (4).

Abstract: A fitting is provided to fix a vertical tail stabilizer of an aircraft to a composite skin and a composite frame of the aircraft in an area of a rear fuselage thereof. The fitting includes a first composite piece having lugs to attach to the vertical tail stabilizer and having vertical walls to fix the fitting to the composite frame of the rear fuselage. The fitting further includes at least one pair of additional composite pieces, each having a horizontal wall to fix the fitting to the composite skin of the rear fuselage. A second pair of additional composite pieces may be provided to further secure the fitting to the skin of the aircraft.

Abstract: The invention provides according to one aspect an aircraft, comprising a fuselage, an airfoil mounted to the fuselage and a flap for steering the aircraft. Furthermore, connecting means articularly connect the flap to the airfoil such that the flap is allowed to rotate around a rotation axis substantial parallel to the trailing or leading edge of the airfoil between a retracted position and an extended position and to translate in a direction substantially parallel to the rotation axis. A rod articularly connect the flap to the airfoil or to the fuselage, wherein the rod defines the translation of the flap in the direction parallel to the rotation axis. Hence, by way of one aspect of the invention, forces acting of the flap in a direction parallel to the rotation axis can be taken up by the rod.

Abstract: An aerodynamic body with an outside with a top and bottom in relation to the direction of airflow, with lateral end parts that form the lateral ends of the aerodynamic body when viewed across the direction of airflow, where in the interior of the aerodynamic body a duct with an airflow drive with a drive motor and a compressor means that is driven by the aforesaid and that is arranged in the duct is arranged, with at least one inlet at the bottom and/or at at least one of the lateral end parts of the aerodynamic body and with at least one outlet at the top of the aerodynamic body for influencing the airflow at the aerodynamic body is arranged, where in the duct a sleeve is arranged which is rotatable by means of a drive motor, which sleeve includes at least one recess which at a particular rotational position of the sleeve can be made to at least in part coincide with the outlet at the top of the aerodynamic body so that the air that has been compressed by the compressor flows through the recess in the sleeve

Abstract: The invention relates to a fuselage cell structure of an aircraft for the simplified installation and attachment of at least one fastener for at least one conduit, the fuselage cell structure having a large number of reinforcing elements formed in particular using an aluminum alloy material. According to the invention, the reinforcing elements within the fuselage cell structure are provided with at least one groove in which the fasteners can be secured by producing a combined pressing and clamping fit creating a positive fit at least in certain regions. For this purpose, the fasteners can have at the lower face thereof, for example, two retaining feet which can be spread apart and attached by driving a fixing element into the groove. The reinforcing elements are continuous stringers preferably produced by extrusion and cross-bars, the required grooves being simultaneously extruded during the production process.

Abstract: The present invention provides a composite, in particular in the field of aviation and aerospace, comprising an omega-stringer that comprises a comb portion, and a connecting member that is connected at one end to the comb portion of the omega-stringer and can be connected at its other end to a standard coupling member. The idea underlying the present invention consists in forming omega-stringers with a connection zone that, on the one hand, is coupled to the comb portion of the omega-stringer and therefore makes it possible to transfer comparatively high loads and, on the other hand, can be connected to a standard coupling member so as to utilize the advantages of standard coupling members of this type when connecting omega-stringers to other stringers, for example T-stringers or other omega-stringers.

Abstract: The present invention provides an air intake valve for an aircraft and a method for the production of an air intake valve. The air intake valve has an opening region for letting ambient air through into a fuselage inner region of the aircraft and a flap for opening and closing the opening region, the opening region and the flap each having a shape which is capable of forming air vortices on edges of the opening region when ambient air flows through the air intake valve.

Abstract: An attachment structure is provided by which interior equipment components of an aircraft passenger cabin can conveniently be affixed. The attachment structure includes, but is not limited to at least one system support that above the cabin floor extends at least along the spacing of two frame elements. The system support has a longitudinal extension along which it comprises a plurality of attachment means, evenly spaced apart from each other, for affixing interior equipment components, wherein the spacing of the attachment means is smaller than the spacing of the frame elements.

Abstract: An overhead luggage compartment is provided with a mounting for a control unit, having a first, top guide, which is fastened in the overhead luggage compartment. A second, bottom guide extends below and at least substantially parallel to the first guide. The first guide comprises a horizontal, first portion adjoined in an inward direction of the luggage compartment by a second portion, which extends obliquely upwards from the level of the first portion. The first portion of the first guide and the second guide are telescopically extensible in horizontal direction. The second guide is open in the direction of the first guide. A first suspension point is coupled rotatably to the outer end of the extensible portion of the first guide. A second suspension point is disposed inwards of the first suspension point and configured for displaceable engagement with the first portion and the second portion of the first guide.

Abstract: The method of fabricating an aircraft comprises the following steps: fastening two lateral floor portions, each firstly to a fuselage element and secondly to supports that are connected to the fuselage element; and then bringing a middle floor portion between the lateral portions and connecting it to the lateral portions.

Abstract: A power regulator and a process regulator, or a power regulating device for regulating hybrid energy sources are provided for an aircraft. The power regulator and process regulator is equipped such that the requirement of a required means of a consumer is measurable. In this arrangement the power regulating device is equipped such that a first operating characteristic of a first energy source and a second operating characteristic of a second energy source are determinable. By means of the first energy source a first requirement share can be generated, and by means of the second energy source a second requirement share of the required means can be generated. The power regulating device can regulate the first energy source and the second energy source such that depending on the first operating characteristic and on the second operating characteristic the first requirement share and the second requirement share of the required means can be provided to the consumer.

Abstract: A decompression-element fastening system releasably fastens a trim component serving as a decompression element to a supporting structure in an aircraft internal region. The decompression fastening system includes at least one bolt, a screw for pressing the trim component in the direction of the supporting structure, and at least one detent element configured for resilient support on the supporting structure. The bolt has a bolt axis and on a first end at least one detent recess and on a second end a first thread. The screw is connected by a second thread to the bolt. The detent element upon approach of the bolt may slide over the first end thereof and come into engagement with the detent recess. If a predetermined tensile force acting in the direction of the bolt axis is exceeded, the detent element disengages from the detent recess.

Abstract: A method for manufacturing a fiber-composite component with a cladding field and a primary component for reinforcing the fiber-composite component includes the steps of: applying a prepreg semifinished product to a mold to form the cladding field, where in the prepreg semifinished product fibers extend in some sections in a curved manner according to an assumed flow force path in the cladding field of the component to be manufactured; curing the prepreg semifinished product; applying layers of a semifinished textile product to the cured prepreg semifinished product to form the primary component; impregnating the semifinished textile product with matrix material; and curing the assembly comprising pre-cured prepreg semifinished product and semifinished textile product; a fiber-composite component with at least one structural component and a skin section connected to said structural component with a recess as well as a fiber-composite fuselage component of an aircraft with a shell component with at least one re

Abstract: An adjusting device for adjusting a flap at an wing of an aircraft includes at least one flap drive for operating the flap and a plurality of drive stations comprising drive struts structured and arranged to movably connect the flap to the wing. The plurality of drive stations includes at least two first drive stations that guide the flap in a defined position in a wing chord direction. The plurality of drive stations includes at least one second drive station at which the flap is moveable in the wing chord direction. The at least one second drive station includes at least one compensation element structured and arranged to compensate constraining forces occurring in the plurality of drive stations due to relative movements between the flap and the wing in the wing chord direction.

Abstract: A large-capacity airplane principally includes a fuselage which has no region of constant width between the front and the rear and a wing fixed to the fuselage. As a preference, the engines are fixed at the rear under a horizontal tail held above the fuselage by vertical stabilizers and maintenance wells are formed in the fuselage in vertical alignment with each engine to allow the engines to be fitted and removed. The width of the fuselage is determined, on the one hand, so that the airplane landing gear is fixed to the fuselage and in the up position is included within the interior volume of the fuselage and, on the other hand, so that the rear engines are above the fuselage in order to make use of the beneficial effects of this position.

Abstract: A control and monitoring system is provided in the aircraft cabin and controls a reconfiguration process with corresponding software in combination with reconfiguration data received from the ground personnel. The control is realized, for example, with a suitable light signals and the unlocking of the seats at certain times. All work sequences are acoustically and/or optically displayed such that the reconfiguration can also be carried out by untrained personnel.

Abstract: An electronic card (4) comprising a processing unit (7), able to receive a command originating from a diagnostic module (6) and a command originating from a simulation system (3). The electronic card (4) comprises means of managing the execution priority of the command originating from the simulation system (3) relative to the command originating from the diagnostic module (6). A diagnostic system of an electronic card comprising a diagnostic module and means of managing the execution priority of the commands. A simulation method is associated with the electronic card (4). For use in particular for analysing malfunctions on electronic cards (4) incorporated in integration simulators (1).