Abstract: The invention relates to a method for protecting a multi-phase autotransformer for an aircraft, including the steps of receiving (100) values of current output from (Ia, Ib) the first and second phases and a value of current input into (IB) the second phase; determining (101), from these received values of the second phase, a value of current representative of the operation (IFb) of the second phase; determining (102), as a function of this determined value and of the value of current output from (Ia) the first phase, a value representative of the homopolar current (Idet-a) flowing in the first phase; comparing (104) this value of homopolar current (Idet-a) with a first predetermined threshold value (S1) at least during a first predetermined period (D1); and controlling (106) the values of currents input into (IA, IB) and/or output from (Ia, Ib) the phases as a function of the said first comparison.

Abstract: An exemplary embodiment of the present invention provides a compartment for accommodating at least one flight crewmember, comprising a first module and a stowage area, wherein the first module comprises a first rest facility, wherein the first rest facility is arranged substantially perpendicular to the longitudinal axis of the aircraft, as well as substantially parallel to the traverse axis of the aircraft, and wherein the stowage area is substantially arranged under the first rest facility.

Abstract: Manufacturing of a composite component, such as a composite component of an aircraft, is provided with a molding tool that includes, but is not limited to a first mold, a second mold and a pressure generator. Between the first mold and the second mold, a membrane is arranged so that between the first mold and the membrane a first region is formed, and between the second mold and the membrane a second region is formed. In the first region, a fibrous mat is arranged. In the second region with the use of the pressure generator 116 counter-pressure can be produced so that the membrane is pressed in the direction of the fibrous mat.

Abstract: An aircraft pylon support system for mounting and supporting aircraft propulsion systems to a fuselage section of an aircraft that includes an internal, central support box disposed within and extending across the interior of an aircraft fuselage, and external support boxes extending laterally into pylons disposed at both sides of the aircraft, each of the internal and external support boxes being made of a composite material and structured as multi-spar boxes containing lateral spars and at least one central spar, wherein the central and lateral support boxes are connected together to provide a continuous interface therebetween with a full transfer of loads therebetween and between any interrupted, intermediate frame members.

Abstract: An aerofoil connection on a fuselage airframe comprising a plurality of double-jointed coupling members. In each case at least two z-coupling members extending substantially parallel to a vertical axis of the aircraft and in each case at least two xz-coupling members are arranged in the region of two longitudinal edges of a fuselage airframe recess wherein the xz-coupling members are configured in each case for a first maximum of a load in the event of a crash and of a load in normal flight operation parallel to a longitudinal axis of the aircraft, and for a second maximum of a load in the event of a crash and of a load in normal flight operation parallel to the vertical axis. The xz-coupling members are capable of absorbing force components parallel to the x-axis as well as force components which arise parallel to the z-axis.

Abstract: An electric flight control system onboard an aircraft provided with flight control surfaces and controllers for controlling these surfaces, that include at least one local electro-hydraulic generator to supply hydraulic servocontrols connected to flight control surfaces.

Abstract: The present invention provides a digital signal processor, a communication system comprising such a digital signal processor and a method for operating such a digital signal processor. The digital signal processor for a communication system in an aircraft cabin of an aircraft comprises a provision means for providing a predeterminable digital signal suitable for forming a respective wave form for mapping a respective pre-determined service signal and a pre-determined noise signal.

Abstract: A door for crew rest compartments of cabins of means of transport comprises a lateral door leaf and a front door leaf as well as a floor element. With the door closed the floor element forms a continuation of the floor of the crew rest compartment. When compared to sliding doors, the cost of manufacture and the weight may be reduced.

Abstract: An avionics device able to be installed on board an aircraft, including means of processing information and a connector able to receive and/or transmit information, the aforementioned connector including an electrical coupling interface able to transmit and/or receive information in the form of electrical signals, and an electro-optical connection interface able to convert electrical signals into optical signals and to transmit information in the form of optical signals and/or receive information in the form of optical signals and convert these optical signals into electrical signals.

Abstract: Disclosed are methods for firmly joining fiber-reinforced, plastic-based adherends, wherein depressions are introduced into opposing lateral surfaces of the adherends, and have injected into them a fiber-reinforced plastic material that serves as an adhesive, a device for implementing such a method, as well as a component joined in this way.

Abstract: The invention relates to the automatic detection of the presence of non-authorized persons in the vicinity of an apparatus of the aircraft type. To this end, the invention comprises equipping persons with radio transmitters for identifying them as authorized personnel. The aircraft are also fitted, such as at the existing PODs, with a transceiver device of a radio identification system of the RFID type for recognition of the persons wearing the radio transmitters. Only the persons who are not authorized in the vicinity of the aircraft initiate an alarm procedure.

Abstract: A Sandwich panel with a core structure, in particular with a honeycomb-shaped core structure, and plane-parallel cover layers applied to both sides of this core structure, to form a floor surface in a fuselage airframe of an aircraft, the core structure having at least one recess into which at least one reinforcing structure is integrated, wherein the at least one reinforcing structure is formed with at least one core, said core having at least one recess into which a stopper is introduced, into which at least one attachment element can be introduced to attach at least one further component to the sandwich panel, and a plurality of prepreg strips which each have a uniform fiber running direction being wound around the core. In addition, the invention relates to a method for the production of a sandwich panel according to the invention.

Abstract: A press device for the energy-efficient curing of a sandwich component for an aircraft, includes an open and mechanically adequately loadable core structure with cover layers applied to one side or to both sides. The sandwich component is restrained between a pressure piston, an abutment and sidewalls of the press device, thus forming an essentially closed interior space. At least one of at least one cover layer and the core structure includes a curable duroplastic plastic material. A conveying device feeds heated air through the core structure of the sandwich component in a closed heated-air circuit or preferably in an open heated-air circuit in order to ensure energy-efficient curing of the sandwich component from the inside out. The heated air is temperature-controlled by a heater. In the case of an open heated-air circuit, heat recovery by a heat exchanger is provided.

Abstract: A device for the protection against the rupture of pipes carrying a fluid includes two or more flow channels and a closing element which interrupts the flow of fluid if a predetermined permissible volume flow is exceeded. At least one of the flow channels can be closed by a test closure in order to increase the flow speed in the remaining flow channels and for test purposes to bring about a movement of the closing element into the closing position. In this way, devices for the protection against the rupture of pipes integrated into complex systems carrying a fluid can be tested in situ to verify their proper functioning.

Abstract: The invention relates to a cover panel for a landing gear for an aircraft with at least one pivotal closable flap 6, 7. According to the invention the at least one flap 6, 7 is attached for swivel movement to the fuselage cell 2 of the aircraft by means of at least one multi-articulated joint 8, 9, 13 wherein the multi-articulated joint 8, 9, 13 is constructed with a number of individual joints seated on a shaft 17, similar to a piano hinge, and a mechanical play increases preferably uniformly starting from a middle individual joint 14 towards the outer individual joints 15, 16. As a result of the mechanical play which increases within the multi-articulated joint 8, 9, 13 from the middle individual joint 14 to the two outer individual joints 15, 16 in the direction of the x-axis or aircraft longitudinal axis, a substantial mechanical isolation of the cover panel from any possible fuselage cell movements is provided.

Abstract: The present invention relates to a display device for a glass cockpit of an aircraft, intended to provide video streams to a plurality of viewing screens of said glass cockpit, said aircraft being partitioned into a secured area, a so-called avionic world (AW), and a non-secured area, a so-called open world (OW), said system comprising at least one first port intended to receive first data to be displayed from a system (210, 310, 410) belonging to the avionic area and at least one second port intended to receive second data to be displayed from a system (220, 320, 420) belonging to the open world, the display device comprising: predetermined hardware resources allocated to the processing of the second data; a processor (241, 341, 441), belonging to the avionic area, adapted to controlling the hardware resources used by said processing and interrupting this processing if said hardware resources used exceed said allocated resources.

Abstract: An aircraft including at least one engine having counter-rotating rotors, the engine or at least one of the engines having imbalances associated with at least one ellipse. The aircraft includes at least one vibration damper attached in an arrangement such that, at a given engine speed and for at least one given common direction of a large axis of the ellipse or at least one of the ellipses, a speed related to the two ends of the damper is higher than for any other arrangement of the damper.

Abstract: An aircraft engine attachment configured to be inserted between an engine and an EMS, the attachment including a plate assembly connected to a first fixing device including an end fitting with two arms and a pin passing through the plate assembly and the two arms, in each of which an orifice is formed including a first ring and a second ring respectively holding the pin. The first ring includes a bottom acting as a stop for a first end of the pin, and the first attachment device includes a mechanism to stop the pin in translation cooperating with a second end of the pin.

Abstract: An avionic bay with a device for filtering cooling air for aircraft electrical equipment. The device includes at least two filtration grilles provided with apertures and which are disposed successively one behind the other in order to filter the air drawn from a cooling air vein before distributing it to an aircraft electrical equipment item. The apertures of the second grille are offset transversely in relation to the apertures of the first grille.

Abstract: An aircraft leading edge, such as, for example, an air intake (22) of a nacelle (14) of a propulsion unit, includes a coating (26) for the acoustic treatment that includes—from the outside to the inside—an acoustically resistive porous layer that has a determined open surface ratio, at least one alveolar structure, and a reflective layer, whereby the coating (26) integrates a frost treatment system, characterized in that a frost treatment system includes at least one vibration emitter (36).