Abstract: A device for a motorized aircraft includes at least one avionic component positioned in the aircraft, at least one engine interface positioned in the aircraft and at least one engine controller positioned in or near an engine of the aircraft. The at least one engine interface is designed to exchange data between the at least one avionic component and the at least one engine controller. The at least one engine interface is generic and able to communicate with engine controllers of various types that may be mounted on the aircraft. The at least one engine controller is specific to a particular engine.

Abstract: This invention relates to a fluid-cooled electronic equipment item, an avionic rack to receive such an equipment item and an aircraft equipped with such racks. The electronic equipment items are connected to the avionic rack on the one hand electrically (C3-C4) and on the other hand fluidically (36?-37, 45?-44) to a system of pipes (30a, 30b) on at least one cold source for a cooling fluid (30). A heat-dissipating electronic board (35) is equipped with a dissipated-heat collector plate (61-65), in which fluid circulation channels are implemented, connected via quick-disconnect fluidic couplings (42, 39) to quick-disconnect fluidic couplings of the system of pipes. These devices allow the equipment to be removed from or inserted into the rack (32-EE) or the electronic board (35) to be removed from or inserted into the electrical equipment (33-35).

Abstract: Swiveling engines attached to the fuselage by struts, for example to the rear part of the fuselage are used to control the pitch and yaw movements of an aircraft. The swivel axes of the engines are oriented to form a V so that swiveling one engine creates a variation of the vertical and lateral components of the engine thrust. Controlled swiveling of the two swiveling engines makes it possible to generate a component of the resultant thrust in a vertical plane that can be controlled in direction and intensity to generate pitch and yaw torques. The swiveling engines also include pods provided with jet deflection flaps for the engine considered, and the struts are profiled and provided with a trailing edge control surface using ruddervator architecture.

Abstract: A water-transporting line includes an integrated heater system for protection against frost and the appropriate connection, attachment and control elements. A self-heating water conduit segment is provided that has an integrated heating device, which device encloses the outer surface of the water conduit segment. The various segments may be connected mechanically and electrically using corresponding connecting elements.

Abstract: A combined bidet and toilet system is provided for a toilet in transportation having a spray nozzle and a flow rate restrictor. The spray nozzle is adapted to provide a water supply to clean a user on the toilet. The flow rate restrictor is adapted to regulate the water supply on the basis of a water flow rate through the spray nozzle. The spray nozzle is adapted so that it is extensible on the toilet for use.

Abstract: Methods, systems, and computer readable media for automatic connection of software simulation models, for example and without limitation, for engineering simulation use in aircraft development are disclosed. According to one aspect, a method for establishing a communication link between software simulation models includes initiating communication between the software simulation models and a publish subscribe mechanism, classifying a quality of service indicator for each of the software simulation models, comparing the quality of service indicator associated with two software simulation models, and connecting the software simulation models based on the comparison of the quality of service indicators.

Abstract: A network node of a wireless communications network is provided in a means of transportation, for an aircraft, for ascertaining sources of interference, to a system with such a network node, to an associated method for ascertaining sources of interference of a wireless communications network provided in a means of transportation, for the aircraft, and to a computer program for executing the method. The network node includes an interference-power-ascertaining component, for ascertaining an interference power of an interfering radiation emitted from a source of interference, and a transmitting component for wireless or wirebound transmission of the ascertained interference power to a control device for determining at least one of a direction of the interfering radiation and a distance of the source of interference, including the position of the source of interference, on the basis of the ascertained interference power.

Abstract: A method of assembling and shaping a laminate panel. An intermediate member is mounted on a lay-up table and a lay-up is assembling by laying a series of plies onto the intermediate member on the lay-up table. The intermediate member and the lay-up are then removed from the lay-up table and placed them on a shaped surface. The lay-up is then forced against the shaped surface, via the intermediate member, in a manner that modifies the shape of the lay-up to form a shaped laminate panel. Finally the shaped laminate panel is removed from the intermediate member. The lay-up table can thus support the flexible intermediate member during assembly, and can be relatively flat to enable the lay-up to assembled by an automated process.

Abstract: The present disclosure relates to a method for allocating a personal electronic device (PED) to a seat in an aircraft, including of connecting a PED to a wireless network of the aircraft, identifying the PED to a near-field communications device of a seat of the aircraft, matching and assigning the seat to which the PED has been identified to the connection data of the PED to the wireless network of the aircraft, and unlocking seat-based control functions for the PED via the wireless network of the aircraft.

Abstract: A method of controlling a flow rate of inerting gas introduced into a vented aircraft fuel tank, the method comprising: monitoring changes in a quantity of a fuel in the aircraft fuel tank; monitoring changes in the ambient air pressure external to the aircraft fuel tank; and actively controlling a flow rate of inerting gas, {dot over (m)}(I), introduced into the aircraft fuel tank based upon changes in the quantity of fuel in the fuel tank and changes in the ambient air pressure, p. Also, an aircraft including a vented fuel tank, a supply of inerting gas for rendering inert the fuel tank ullage, and a controller for performing the method.

Abstract: A method for assisting the construction and validation of an avionics platform uses, on the one hand, a functional description of the platform using avionics functions, software modules suitable for executing these functions, and functional link occurrences between these modules and, on the other hand, a material description of this platform using calculation or communication items of equipment and physical links between these equipment. The method according to the invention enables to generate paths between the various items of equipment by using direct physical links and/or physical links belonging to one or more network(s), and subsequently to associate at least one such path to be each functional link occurrence. It also enables to associate to each software module an item of equipment adapted to host it.

Abstract: The aircraft passenger seat headrest (20) includes a carrier (21) and a helmet (22) for at least partially housing the head of the passenger. The helmet is attached to the carrier and is movably mounted in relation to the carrier (21). Said helmet includes a body and at least one portion (32, 34) that is movably mounted onto the body to extend the latter.

Abstract: A force measuring system is provided for measuring forces on a rotating body that includes, but is not limited to a force measuring device, which is mounted on the rotating body, as well as a position sensing unit for detecting the rotation of the rotating body and an evaluation unit, which is connected to the force measuring device and the position sensing unit. The evaluation unit is configured for recording a force value measured by the force measuring device depending on the detected position of the rotating body. The force measuring system allows the forces and torques on a rotating body to be determined precisely and as flexibly as possible, independently of the prevailing rotation speed of the rotating body.

Abstract: An aerodynamic aft fairing of an engine pylon ensuring the mounting of an engine underneath a wing of an aircraft is provided. The aerodynamic aft fairing includes an outer lateral panel and an inner lateral panel assembled together at least by a bottom panel, the bottom panel comprising, on either side of the lateral panels, an extension forming an aerothermic barrier capable of channeling hot air flows leaving the engine. The inner lateral panel and the outer lateral panel are attached to the bottom panel by a first angle bar and a second angle bar, respectively.

Abstract: An aircraft fuselage has at least one reinforcement frame (13), at least one crossbar (14) and at least one energy-absorbing structural element (2) that includes a compression beam (21) having a longitudinal axis Z and oriented substantially in the direction of compression forces to be absorbed upon an impact, the compression beam being attached at a first end (213) thereof to the crossbar (14) and at a second end (214) thereof to the reinforcement frame (13). The compression beam (21) is attached at least one of its ends (213, 214) via a shoulder bracket (22), wherein the shoulder bracket further has the function of cutting the compression beam (21) in case of an impact.

Abstract: A method of controlling the center of gravity of an aircraft having a plurality of fuel tanks, the method comprising transferring fuel from one or more of the fuel tanks according to a predetermined sequence, the timing of the sequence being dependent on the decrease in gross weight of the aircraft.

Abstract: A floor can be attached to a vertical frame structure of a vehicle and includes a horizontal boxed structure having a plurality of boxes positioned side by side to form a continuous, uniform upper surface and lower surface, with the upper surface covered with an upper skin and the lower surface covered with a lower skin and means of attachment to attach the boxed structure laterally to the frame structure.

Abstract: A method for guiding an aircraft during its final approach to a landing runway, whereby the aircraft is guided during its approach by aircraft position information obtained from an GNSS satellite navigation system, wherein: prior to the start of the final approach a first time tFAF is determined corresponding with the start of said final approach and a second time tTD corresponding with the landing of the aircraft on said runway, then a set of satellites is determined of the satellite navigation system for excluding from the calculation of said aircraft position information during at least a part of the time interval comprised between said first and second times; and during the final approach, the aircraft position information is determined while excluding the information corresponding with all the satellites of said set of satellites and the aircraft is guided along its final approach path by said position information.

Abstract: A fault-tolerant actuating system with at least one flap, adjustable on a respective wing of an aircraft, and with a control and monitoring device, includes: drive devices that are functionally connected to the control and monitoring device, with one of these drive devices in each case being associated with a flap, where each flap in each case is associated with a drive device, in each case including: two drive motors, two brake mechanisms, where each drive motor is associated with a brake mechanism for stopping rotation of the output of the respective drive motor, a differential that couples the outputs of the aforesaid to the aforesaid in a summing manner, an output shaft for coupling the output of the differential to drive connections, and a differential lock that is functionally connected to the control and monitoring device, which differential lock is coupled to the control and monitoring device in this manner, where each of the brake mechanisms as well as the differential lock can be operated by way of

Abstract: An interface system for use in an aircraft galley includes a first connection element. The first connection element can be connected via a first appliance connection apparatus to an internal electrical system, an internal fresh water supply system, and an internal wastewater disposal system of a first galley appliance, and can be connected via a second appliance connection apparatus to an internal electrical system, an internal fresh water supply system, and an internal wastewater disposal system of a second galley appliance. Further, the first connection element can be connected via an aircraft galley connection apparatus to a complementary aircraft galley connection apparatus of a second connection element of the interface system. The second connection element can be fixed in a compartment in the aircraft galley, so as to connect the first connection element to an electrical system, a freshwater supply system and a wastewater disposal system.