Abstract: A propulsion engine comprising at least a first propulsion unit including a first fan encased by a geared ring and a gas turbine engine driving a first shaft connected to the first fan, at least a second propulsion unit including a second fan encased by a geared ring connected to a second shaft operatively coupled to an electric machine and at least an electric storage device connected to the electric machine. The geared rings are configured to transmit torque between the fans so that they can rotate in conjunction (directly or through an intermediate gear) when they are driven by at least one of said first and second shafts. The propulsion engine is arranged for controlling the torque to be supplied to the assembly of the first and second fans by the gas turbine engine and/or by the electric machine acting as a motor or as a generator.

Abstract: A sandwich structure architecture for high speed impact resistant structure includes sandwich skins which enclose a sandwich core formed by a plurality of spacing layers and a plurality of trigger layers, wherein these layers are stacked alternatively in the core. The walls of the trigger layers are thicker than the walls of the spacing layers and/or the walls of the trigger layers include at least one part inclined with respect to the walls of the spacing layers. The spacing and the trigger layers are made of the same type of material, preferably composite materials or metallic materials. The structure is capable of absorbing high-speed impacts, and at the same time can be used as load carrying structure in aircraft fuselages, wings, vertical or horizontal stabilizers.

Abstract: The present invention provides an actuator comprising an actuator body, a piston relatively moveable within the actuator body, and a rod attached to the piston and extending out of the actuator body, the actuator body comprising a port for conveying actuator fluid, wherein the actuator also has a damping control portion provided with damping control fluid containing magnetic particles, wherein the piston or the rod is adjacent the damping control fluid, and a first electrical coil associated with the damping control portion, such that an electrical current supplied to the first electrical coil induces a magnetic field and causes the effective viscosity of the damping control fluid to increase, thus increasing the damping effect of the damping control fluid on the piston or rod. The invention also provides an aircraft assembly, such as a landing gear assembly, an aircraft and a method of operating an actuator.

Abstract: An adapter for tapping into an aircraft panel network in order to provide support for a wireless flight attendant panel (FAP). The adapter includes first and second connectors to insert into the server-to-FAP connection of the panel network and a third connector configured to connect to a wireless access point. The adapter has a housing to which the first, second and third connector are mounted, wherein the housing accommodates power and data connections between the first and second connectors as well as a panel network access connection line between the first connector and the third connector, thereby enabling connection of the panel network to a wireless access point.

Abstract: A method of bonding two components at a joint interface using a UV-curable substance. The method comprises incorporating a UV radiation emitting device in the joint interface between the components together with said substance and supplying power to said UV radiation emitting device to generate UV radiation and cure the substance.

Abstract: The present invention relates to structural component for an aircraft. The structural component comprises a body with a first surface and a lug that extends out of the first surface. The body and lug comprise a composite material and are integrally formed.

Abstract: An on-board system for evaluating the severity of a lightning strike, intended to be installed in the interior of an airplane and connected to an avionic system of the airplane. The system comprises four devices, a master device and three slave devices, each device comprising a magnetic-field sensor. The devices are placed pairwise symmetrically about a plane of symmetry of the airplane, vertically in line with the leading edge of the wing of the airplane and vertically in line with the trailing edge of the wing, respectively. The system allows an evaluation of the severity of a lightning strike to be obtained depending on the measured magnetic fields.

Abstract: A coupling device for supporting a first wing section against a second wing section of an aircraft, and configured for passive flight load alleviation includes a housing including a chamber including a first portion and a second portion and filled with a fluid, a piston device movably arranged in the chamber and separating the first portion from the second portion in a fluid tight manner, a first fluid pathway connecting the first portion to the second portion, a first pressure relief valve arranged in the first fluid pathway and blocking the first fluid pathway, if the pressure in the second portion is smaller than a first relief pressure and opening the first fluid pathway, if the pressure in the second portion is greater than the first relief pressure. In addition, the coupling device can be used to actuate the second wing section against the first wing section.

Abstract: A self-destruction device adapted to be installed in a propeller blade, the self-destruction device including a detector adapted to detect a release of the propeller blade, a warning mechanism adapted to send a release alarm in the event of the detector detecting release of the propeller blade, and a destruction mechanism adapted to destroy the propeller blade in the event of receiving a release alarm from the warning mechanism. An engine and an aircraft are also provided.

Abstract: A tooling assembly for integrating a central part of the fuselage of an aircraft. The tooling assembly comprises a tooling train which comprises a succession of movable carriages arranged behind one another and which are able to carry one or more items of aircraft equipment to be integrated into the central part of the aircraft. Such a tooling train, which extends over at least a length of the central part of the fuselage, makes it possible to integrate, at the same time, items of aircraft equipment produced in the form of elongate modules, thus reducing the time for integrating the items of aircraft equipment.

Abstract: A method and portable apparatus for servicing a shock absorber on a landing gear assembly of an aircraft in a weight-on-wheels state is disclosed. The shock absorber includes at least one chamber containing both hydraulic fluid and a gas in fluid communication with each other. The apparatus includes a source of gas and a source of hydraulic fluid. The amount of hydraulic fluid in the chamber is corrected, preferably such that the chamber is then filled with a known amount of degassed hydraulic fluid. A pre-set mass of gas is then delivered into the chamber under the control of a gas delivery system of the portable apparatus. More accurate servicing of a shock absorber may thus be provided since account is additionally taken of gas dissolved in hydraulic fluid. By delivering a pre-set mass of gas into the chamber, there is no need to rely on a measure of gas pressure or H-dimension (h) when servicing the shock absorber.

Abstract: In order to bring a turbofan engine closer to the lower surface of a wing box, the disclosure herein foresees an assembly for an aircraft including a mount for mounting a rigid structure of an engine strut to the wing box, the mount including an upper wing mount including a fitting secured to the upper surface of the wing box.

Abstract: The invention relates to an actuator. More specifically, but not exclusively, an aircraft pitch damper which comprises an actuator. The actuator comprises a first chamber charged with gas and a second chamber charged with gas. An intermediate chamber containing liquid is located between the first chamber and second chamber. A piston rod extends towards the first chamber through the second chamber and intermediate chamber. A first piston head is associated with and partially defines the first chamber, and a second piston head is associated with and partially defines the second chamber. The piston rod is arranged to abut and move with the first piston head in a first direction, the piston rod further arranged to abut and move with the second piston head in a second direction.

Abstract: The disclosure herein proposes identifying precursors to all the phenomena which can have an impact on the service use of an aircraft. It relates to a system for predicting failures in an aircraft, including a processor configured to analyze a current behavior of at least one flight parameter of the aircraft to detect any deviation of the current behavior relative to a predetermined behavior model of the parameter, the behavior model being determined from a plurality of series of learning data relating to the parameter collected during the flights of a set of aircraft.

Abstract: The present disclosure refers to a method for measuring thickness in any type of carbon fiber component, even in components having parts with different thickness and integrating at least a second material. The method includes measuring with the maximum and minimum real thickness of the component, and measuring with ultrasonic equipment the time that the ultrasound takes to propagate across the component part with maximum and with minimum thickness, calculating a thickness correction value, and calculating an ultrasound test speed from said thickness correction value, said measured times, and said measured maximum and minimum real thickness. Then, the total thickness of each of the parts of the component are measured, using ultrasounds with the same calculated ultrasound test speed, and the thickness correction value is applied to each of the measuring total thickness of each part, to determine a corrected carbon fiber thickness for each part.

Abstract: An aircraft engine pylon includes two side panels and an upper stringer and a lower stringer assembled to form a strut assembly extending in a longitudinal direction (AX) corresponding to the direction in which the aircraft is moving and an internal reinforcement structure including a plurality of reinforcements. The pylon also includes a reinforcement zone on each side panel and a front housing to receive a main front center reinforcement and a rear housing to receive a main rear center reinforcement.

Abstract: A system for moving loads comprising a cargo hold floor with a plurality of guide rails, and a plurality of transport vehicles removably received in the guide rails and being movable along the guide rails and which each comprise a carrier face movable perpendicularly to a surface of the cargo hold floor, between a first and a second operating position. The carrier face is arranged, in its first operating position, such that the transport vehicle received in a guide rail is positionable under a load which is deposited, at least partly, on the surface of the cargo hold floor. In its second operating position, the carrier face is arranged such that it lifts the load off the surface of the cargo hold floor and carries it. In the region of the carrier face, there are provided a plurality of rollers adapted to permit movement of the load parallel to the surface of the cargo hold floor.

Abstract: An aircraft air conditioning system includes an ambient air line connected to an air conditioning system mixer to supply ambient air, and a cabin exhaust air line connectable to an aircraft cabin for being flown through with cabin exhaust air. An ambient air compressor in the ambient air line compresses ambient air in the ambient air line. A refrigerating apparatus includes a refrigerant circuit and a refrigerant compressor in the circuit. The refrigerant circuit is thermally coupled to the ambient air line to transfer heat from ambient air line air to refrigerant circulating in the circuit before the ambient air is supplied to the mixer. A turbine is coupled to the air compressor. A control device controls the air conditioning system wherein in a first operating state the turbine receives air from the ambient air line, and in a second operating state receives cabin exhaust air.

Abstract: Multiple-core processor to be connected, by way of communication ports, to a deterministic switched Ethernet network using virtual links to which items of equipment are connected, the processor including clusters each including cores, wherein at least one cluster of the processor implements a switch function that makes it possible to interconnect the items of equipment in the network. At least one cluster of the processor implements an end system function providing functions of sending and receiving data in the network, and at least one cluster of the processor implements an application.

Abstract: A method, system and dispensing head for manufacturing a three-dimensional object by additive manufacturing. The three-dimensional object includes a three-dimensional component. The method provides a substrate and forming layers there-on, each layer formed in a pattern corresponding to a three-dimensional component being manufactured and each layer formed by dispensing a curable material from a nozzle of a dispensing head and subsequently curing the curable material. The three-dimensional object comprises the combination of the substrate and the three-dimensional component, wherein the substrate has a non-planar surface portion and the three-dimensional component is formed on the non-planar surface portion such that it is fixedly secured to the substrate.