Abstract: A pressing-on device for pressing fiber-reinforced thermoplastic materials onto a mold is described. The pressing-on device has a main body and a pressing-on layer provided on a surface of the main body. The pressing-on layer is implemented in this case using an inorganic material, preferably a ceramic material, and has a flexibility because of its structure which allows it to adapt itself to the contour of a mold. Increased heat resistance of the pressing-on device and improved properties of the processed fiber-reinforced thermoplastic material can be achieved.

Abstract: The invention concerns a method of connecting a first material to a second material by means of a heat-activatable adhesive material (8) in aircraft construction, wherein the adhesive material (8) is arranged between the first material and the second material and an induction heat which is adequate to activate the adhesive material (8) is generated. The first material and/or the second material and/or the adhesive material (8) have an induction heat-generating means. The induction heat-generating means is a non-woven metallic mesh and/or the induction heat-generating means (53) has an amount of carbon fibers for induction heat generation. The invention further concerns an apparatus comprising a first material and a second material, wherein the first material and the second material have a connection which can be produced by a heat-activatable adhesive material arranged between the first material and the second material, in accordance with the method in accordance with the invention.

Abstract: Methods and devices for non-intrusive identification and communication between a server node and at least one client node in a communication network. An identification message is first transmitted to at least one client node, the identification message including at the application level a duplicate of the addressing data, the physical address and the internet address of the server node, also contained in the MAC and IP layers. The reception of at least one couple of addresses from at least one client node, wherein a couple of addresses from a client node includes a physical address and an internet address according to the same duplication strategy, can be used for identifying the client node by the server. Similarly, the methods and devices can be used for identifying in a client node at least one server node in the network.

Abstract: An engine assembly for an aircraft, including a rigid structure including a box rib extension protruding from a box of the structure, in a line of separation, towards a fuselage of the aircraft. The extension supports a first attachment in a position separating it from a second attachment in the line of separation. The first and second attachments enable the moment being exerted in a lengthways direction of the turbine engine to be transmitted jointly.

Abstract: A method is described for optimized energy management of an aircraft upon a flight along a trajectory. The method allows the aircraft to join a given point of the trajectory in a given energy state, with a given position of the slats and flaps, and with a given position of the landing gear. The method includes determining current parameter values of the aircraft. The method also includes determining optimized command orders based on the current parameter values by performing a sequence of operations in an iterative way. The method further includes applying the optimized command orders to an automatic slats and flaps command device and an automatic landing gear command device for automatic control of the slats and flaps and the landing gear, respectively.

Abstract: A folding passenger seat and a corresponding passenger seating system for means of passenger transport are provided. The folding passenger seat comprises a seat frame, on which a front seat leg having a first fastening element and a rear seat leg having a second fastening element are arranged. The first fastening element and the second fastening element are configured to be connected to rails on a cabin floor of the means of passenger transport and to be displaced in the rails. A first joint element is arranged between the first fastening element and the second fastening element such that a spacing between the first fastening element and the second fastening element is variable. In particular, the first joint element may be arranged between the front seat leg and the seat frame or between the rear seat leg and the seat frame.

Abstract: A control device for activating an oxygen system of a means of transport, in particular an aircraft, a control system having such a control device, an associated method for activating an oxygen system of a means of transport, in particular an aircraft, and a computer program for carrying out the method. Furthermore, a network is provided for a means of transport, in particular for an aircraft. The control device for activating the oxygen system comprises a first activation unit which is configured to activate at least a part of the oxygen system by wireless transmission of a first activation signal.

Abstract: Methods and devices for improving the reliability of communication between an aircraft and a remote system. The aircraft transmits a request for verification of security to a remote system. Upon reception of the response to this request, which includes at least one indication pertaining to the security of the remote system, the aircraft analyzes this indication and decides to establish or not to establish data communication between the aircraft and the remote system. When a verification request is received, the remote system is verified and a response to the request is transmitted to the aircraft.

Abstract: An insulation device for an aircraft, comprising a blanket comprising a layer of insulation filling enclosed in a cover and having provision areas for the passage of aircraft components, these areas being devoid of insulation filling and being formed by a surface junction of two opposite faces of the cover inducing a recess in at least one face. The insulation device comprises an associated detachable complementary assembly to cover at least one of the provision areas, the assembly comprising a portion of insulation filling shaped to fit into the corresponding recess, and a retention arrangement for retaining this portion of filling. The retention arrangement is provided with a detachable arrangement for fixing the detachable complementary assembly on at least one face of the cover.

Abstract: A bearing assembly for mounting a pair of spaced parallel actuators between a wing and a control surface of an aircraft so that the actuators control deployment of the control surface from the wing in tandem. The bearing assembly includes a fixed member for attachment to the aircraft and a movable member attachable to the actuators. The fixed and movable members are coupled via a part-spherical bearing and are configured such that the part-spherical bearing is located in the space between the actuators.

Abstract: A water system for a vehicle is provided. The water system comprises at least one water supply source, at least one water-conducting device, at least one closing valve and at least one germ reduction connection. The germ reduction connection and the water supply source are connected to the water-conducting device. The germ reduction connection is designed to introduce a germ-reducing fluid into the water-conducting device. The closing valve is arranged between the water supply source and the germ reduction connection and is designed to be fully closed thus preventing the ingress of germ-reducing fluid into the water supply source. By means of such a water system it is possible to carry out sterilization or disinfection very easily and quickly without this requiring any major maintenance work.

Abstract: An apparatus for producing a component includes a material storage tank for receiving a liquid material (M), a molding tool in which a filling region to be filled with material (M) from the material storage tank is formed, and a material supply line which connects the material storage tank to the filling region of the molding tool. In the region of the material supply line and/or the filling region of the molding tool an optical fiber has been arranged, into which at least one Fibre Bragg Grating sensor for detecting a parameter that is characteristic of the flow of material through the material supply line and/or the filling region of the molding tool is integrated.

Abstract: A tool for a resin transfer molding method comprises a cavity, a resin trap and a transition region, wherein the cavity is designed such that a component can be accommodated in it. Furthermore, the resin trap is integrated in the tool, and the transition region is designed such that with it a connection between the cavity and the resin trap can be established.

Abstract: The invention pertains to a de-icing system for an aircraft with at least one heat source and at least one air delivery means for delivering air into regions of the aircraft to be de-iced. In comparison with the prior art, the invention is characterized in that the air delivery means is connected to an air-conditioning system of the aircraft for discharging air from the cabin of the aircraft via an air heating device, wherein the air heating device is connected to at least one heat source in order to heat the air from the cabin of the aircraft. The de-icing system according to the invention is able to realize a wing de-icing that not only fulfills an anti-icing function, but also a de-icing function on the ground without additional expenditure of energy.

Abstract: Radiocommunication system for aircraft. The radiocommunication system (S1) comprises a single box and, integrated into this single box, at least one single main interface module (7), which is formed in such a way as to carry out the processing of the interfaces of all the radiocommunication means (3 to 6) of said radiocommunication system (S1).

Abstract: An aircraft cooling system including a cooler which is adapted to supply cooling energy to an aircraft device to be cooled, and a heat transfer arrangement which is adapted to transfer waste heat generated by the cooler to a cabin air extraction system. The heat transfer arrangement comprises a heat transfer circuit, in which a liquid heat transfer medium heated by the waste heat of the cooler circulates.

Abstract: A crew rest compartment for a means of transport includes a first bunk and a second bunk, wherein the first bunk is located above the second bunk. Each bunk includes a sleeping area for accommodating a sleeping crew member, wherein each sleeping area has a longitudinal direction. The first bunk is aligned such that the longitudinal direction of the first bunk and a longitudinal direction of the crew rest compartment enclose an angle which differs from 0° and 90°.

Abstract: An aircraft cooling system including a cooler having a cold transfer circuit, in which a cold transfer medium circulates. The cooler supplies cooling energy to an aircraft device to be cooled. The aircraft cooling system further includes a heat transfer arrangement having a heat transfer circuit, in which a heat transfer medium circulates and which is thermally coupled to the cold transfer circuit of the cooler via a heat exchanger, in order to absorb waste heat generated by the cooler and transfer it to a cabin air extraction system. The heat transfer arrangement further includes at least one heat pump which brings about an increase of the heat energy transfer from the cold transfer medium circulating in the cold transfer circuit of the cooler to the heat transfer medium circulating in the heat transfer circuit, at least in certain operating phases of the aircraft cooling system.

Abstract: An aircraft air-conditioning system including an air-conditioning unit which is designed to provide cooled process air. A process air line conducts cooled process air provided by the air-conditioning unit into a working area of an aircraft cabin. A cooler supplies cooling energy to a device to be cooled which is provided in the working area of the aircraft cabin. Finally, the aircraft air-conditioning system includes a heat transfer arrangement which transfers waste heat generated by the cooler to process air flowing through the process air line.

Abstract: An aircraft nacelle that makes it possible to channel a stream of air in a longitudinal direction and that includes at least two panels (50, 50?) placed end to end in the longitudinal direction, each including a so-called aerodynamic surface (52, 52?) that is in contact with the air stream and an edge (54, 54?) that is in contact with the edge of the other panel, characterized in that at least one of the panels includes—at its edge (54, 54?)—at least one partition (58) that projects relative to the edge that extends in the direction of the edge of the other panel, in a manner that is secant to the aerodynamic surface and in a plane that contains the longitudinal direction, so as to limit the circulation of air between the edges of the panels.