Abstract: A drive system for rotating a wheel of an aircraft landing gear includes a motor operable to rotate a first drive pinion via a first drive path and a driven gear adapted to be fixed to the wheel. The drive system has a first configuration in which the first drive pinion is capable of meshing with the driven gear to permit the motor to drive the driven gear via the first drive path. One of the first drive pinion and the driven gear comprises a first sprocket and the other of the first drive pinion and the driven gear comprises a series of rollers arranged to form a ring. Each roller being rotatable about a roller axis at a fixed distance from an axis of rotation of the first drive pinion or driven gear, respectively.

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 method of joining a first component to a second component, the method comprising preparing the first component by forming an array of projections extending from a bond surface of the first component, each projection having a base, a tapered tip and a tapered overhang beneath the tip, wherein the overhang has an undercut surface which is inclined and faces towards the local bond surface; bringing the components together so as to embed the projections in the second component; and hardening the second component after the array of projections has been embedded into it. Also, a joint so formed.

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: The object of the invention is in particular a device for execution of applications (510) in an aircraft information-processing system (500), permitting the simultaneous execution of at least two distinct applications, the said information-processing system comprising shared calculation and storage resources. The device comprises software segregation means capable of creating at least two distinct information-processing environments (505), a partition of the said calculation and storage resources being allocated to each of the said at least two environments in such a way that the execution of one of the said at least two applications in one of the said at least two environments does not have any effect on the execution of the other of the said at least two applications executed in the other of the said at least two environments. Another object of the invention is a method for employing such a device.

Abstract: The device includes processor elements for determining an optimal flight trajectory, which is free of collision with obstacles, which respects constraints of energy, and which links the current position of the aircraft to a target point defined by an operator. The device minimizes additional crew work required to update and validate a new trajectory when an original flight plan needs to be modified to avoid moving obstacles such as storms or other aircraft.

Abstract: The present invention relates to a production method for a workpiece composed of a fiber-composite material, having the following steps: at least one support means is provided. A main material composed of a pre-impregnated fiber semi-finished product and/or of a secondary material are/is applied to the at least one support means in order to form at least two blank-mold areas, in such a manner that at least one of the at least two blank-mold areas has the main material, and at least one of the blank-mold areas has the secondary material. The blank-mold areas are pressure-bonded to one another to form a workpiece blank such that the at least one support means is provided on a surface of the workpiece blank. The at least one support means and the secondary material are removed from the workpiece blank in order to form the workpiece.

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: 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 picocell in an aircraft for the wireless transmission of data between at least a mobile station in the aircraft and a base station in the aircraft in which a communications connection between the at least one mobile station in the aircraft and a subscriber in a terrestrial communications network is established via the base station. In order to enable passengers automatically the use of their mobile radio devices, when no risk of danger to the flying operation is to be expected, or otherwise to refer them to a corresponding ban, a flight control device is provided for detecting flight data and for setting up the picocell in dependence on the flight data.

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: 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: A ceiling panel is configured for attaching a curtain in a cabin of a transportation device with an attachment unit, a mounting unit, and a curtain attachment unit. The ceiling panel is configured to integrate the attachment unit, the attachment unit is configured to attach the mounting unit to the ceiling panel, the mounting unit is configured to attach the curtain attachment unit, and the curtain attachment unit is configured to support the curtain.

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: In the method of accessing an information system of an aircraft the system receives an authenticator request from a connector of the aircraft; the system determines whether the connector presents a predetermined characteristic; and in the event that the system determines that the connector does indeed present the predetermined characteristic, the system sends an authenticator to the connector. Provision is also made for: the system receives an authenticator the system determines whether the authenticator is valid; and in the event that the system determines that the authenticator is indeed valid, the system authorizes access to the system from a connector of the aircraft from which the authenticator was sent.

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 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 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: Pultrusion methods and apparatus for manufacturing a profiled preform or FRP-component with cross-sectional segments that extend angularly to one another from a plurality of semifinished products in a quasi-continuous process, where: at least one multilayer semifinished product arrangement [of a multilayer semifinished product arrangement] is dispensed from a dispenser unit in order to manufacture the preform, with the multilayer semifinished product arrangement dispensed from the dispenser unit being fed to the forming device and including a combination of several webs of semifinished reinforcement fiber layers and at least one resin film; the semifinished product arrangement is guided through a forming device and at least one cross-sectional segment of the semifinished product arrangement is angled in order to form an angle profile, with the semifinished product arrangement being compressed in a pressing device, optionally after a hardening process, and with a longitudinal section of the preform or the comp

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.