Abstract: The invention provides a fan cowl (11) of an aircraft engine made of a composite material having an optimized structure for withstanding the expected loads and for being able to be manufactured as a monolithic ensemble. The structure comprise a skin (13), frames (15) of a closed cross-section arranged in a transverse direction to the longitudinal axis of the aircraft and longitudinal beams (17, 19) comprising first parts (21) of a closed cross-section to be superimposed to the transverse frames (15) in their crossing zones and second parts (23) of an open cross-section in zones not crossing transverse frames (15) having their webs (41) arranged in a same plane. The invention also refers to a manufacturing method of said fan cowl (11).

Abstract: Systems and methods for the calculation of the approach speed during air to air refueling maneuvers. The systems comprise: a) capturing means of a sequence of digital photograms of the approach operation scenario calibrated in order to determine the real distance corresponding to a pixel of a photogram; b) computational means configured for obtaining the coordinates of the relative trajectory of the receiver aircraft with respect of the tanker aircraft, by means of a sequence of photograms of the approach operation obtained by said capturing means and calculating the speed difference between receiver aircraft and tanker aircraft based on the trajectory defined by the coordinates recorded in said process b1). The invention also refers to the methods for calculating the approach speed.

Abstract: An Electrical Power System for supplying electrical power to the loads of a vehicle comprising a Power Generation Area (11); a Primary Distribution Area (13); a Secondary Distribution Area (15) including Electrical Power Load Management Units (EPLMUs) (17, 17?, 17?, 17??) that comprise a Control Board (31) and one or more SSPCs (33) for groups of loads (19, 19?, 19?, 19??); and a master EPLMU (21) that comprise a Control Board (32) and one or more SSPCs (33), powered from the Primary Distribution Area (13) and connected to said EPLMUs (17, 17?, 17?, 17??) by power supply lines and by a data communication bus (26), and a Load Management Computer (25) connected to said data communication bus (26); said master EPLMU (21) and said Load Management Computer (25) being suitable arranged for full control of the start up and the shutdown of said EPLMUs (17, 17?, 17?, 17??).

Abstract: A device and a method for eliminating transitions in discrete signals. The working of the device and method is based on allowing the charge of a capacitor with one state when the state opposite the state to which it has been assigned is produced and allowing their discharge through a corresponding capacitor when their state is active. The signal is advantageously consolidated without needing processors or programs, is very simple, there is increased reliability, and the device can very easily be integrated in any sensor, such as those used in aircraft.

Abstract: A communications system between a receiving aircraft and a tanker aircraft. The system includes a retractable tube with a nozzle which connects to a receiving aircraft receptacle, wherein the system comprises a primary device for sending/receiving data on the nozzle and a secondary device for sending/receiving data on the receptacle. The tanker and receiving aircraft transmit data by means of the devices only when the devices are both active and positioned opposite each other. In this way an indication is enabled to at least one of the two aircraft that the nozzle is correctly connected in the receptacle.

Abstract: A telescoping tube for fuel transfer operations has a fixed part and a moving part, the moving part further having a dynamic sealing system which guarantees the sealing of the moving part against the fixed part, a cushioning system which absorbs the energy of the impact of the moving part against the fixed part in operations for extending and retracting the tube and protection systems against electrical discharges which ground the moving part to the fixed part, the aforementioned dynamic sealing, cushioning and protection systems all being incorporated in a single unit in the moving part of the telescoping tube. Additionally, the invention relates to an in-flight refuelling system for a tanker aeroplane, to carry out in-flight fuel transfer operations to a receiving aircraft, having a telescoping tube with the abovementioned characteristics.

Abstract: A method and system of monitoring a structure, the method including: a) synchronously acquiring data comprising a plurality of operational parameters and at least one strain data, b) building a significant points dataset from the data acquired in step a), and c) modelling a relationship between the operational parameters and the strain data using the built significant points dataset to train a non-adaptive prediction functional supervised approximation method, wherein the step of building a significant points dataset comprises deletion of redundant information from the acquired data. The resultant models may be used to process structure real operation data in order to estimate the eventual crack initiation and crack growth on a set of predefined locations of the structure.

Abstract: A two-stage linear actuator particularly applicable to aircraft control surfaces. The first stage comprises a rotary input shaft driven by an electric motor having a helical threaded zone in its external surface at its inner end and a plurality of first helical roller gears configured to engage with the rotary input shaft in its helical threaded zone for rotating together. The second stage comprises a plurality of second helical roller gears configured to engage with the first helical roller gears for rotating together and with an output shaft having a helical threaded zone in its external surface at its inner end for converting the rotation of the second helical roller gears in a linear movement of the output shaft.

Abstract: A joint attaching a structural element to a composite part comprising a metallic attachment, this joint being subjected to a fire source on one of its sides, the fire side. The joint comprises a retaining device located at the side of the joint opposite to the fire side, the cold side. The retaining device comprises a first surface that is in contact with the metallic attachment, and a second surface which is in contact with the composite part. The second surface has a larger area in contact with the composite part than the area of the first surface in contact with the metallic attachment. The retaining device is made of a material with a high thermal conductivity. Such a joint may be in an aircraft.

Abstract: Adjusting device (1) for an aircraft landing gear shock absorber (2), such that the length (3) of said shock absorber (2) can be varied to change the aircraft attitude for operations on ground, wherein the adjusting device (1) is directly connected to a shock absorber (2) by a supply line (16), the adjusting device (1) comprising an actuating element (13) that moves in a chamber (17) filled with a fluid (20), the actuating element (13) being displaced by means of a drive shaft (12) driven by a driving device (11), the displacement of the actuating element (13) in the chamber (17) causing the addition or removal of fluid (20) in the shock absorber (2), therefore varying the length (3) of said shock absorber (2). The invention also refers to an aircraft landing gear comprising such an adjusting device (1).

Abstract: Reception coupling unit of a hose and drogue device of a tanker aircraft with the probe of a receiver aircraft for in-flight refueling, including, respectively, first and second cooperating latching devices that can be positioned in one or more latching states in a refueling operation, in which the reception coupling unit includes at least a detector of the latching states and at least a first indication device and/or a second indication device for providing, respectively, to the pilot of the receiver aircraft and/or to the crew of the tanker aircraft indications that the cooperating latching devices are positioned in one or more of the latching states, the detector being operatively connected, respectively, to a first indication device and/or to a second indication device.

Abstract: A guiding tool for the drill bit of a drilling apparatus and a method of making drills. The tool includes a body with an orifice for passage of the drill bit and a base with at least three protruding feet for resting on the working surface. The feet are configured with inner holes with an outlet at its ends. The tool is connected to a pneumatic device of pressurized gas supply which includes a signal indicative of correct positioning of the tool for performing a drill when a simultaneous blocking of gas output in said feet is produced when all of them are in contact with said working surface; the tool including a pressurized gas pipeline up to said feet.

Abstract: A device and a method for eliminating transitions in discrete signals. The working of the device and method is based on allowing the charge of a capacitor with one state when the state opposite the state to which it has been assigned is produced and allowing their discharge through a corresponding capacitor when their state is active. The signal is advantageously consolidated without needing processors or programmes, is very simple, there is increased reliability, and the device can very easily be integrated in any sensor, such as those used in aircraft.

Abstract: A workbench and an assistance method for manufacturing or checking electrical wiring harnesses. The workbench comprises: an assembly board; image projection devices on the assembly board; optical sensors arranged on the assembly board to provide information about its position; cameras arranged to capture gestures of the technician in charge of the workbench; a computer with a set of computer programs adapted to provide, through the image projection devices images in 1:1 scale of templates of the electrical wiring harness being manufactured or checked projected onto the assembly board and, superimposed on them, complementary images of aid requested by the technician, acting on virtual menus and/or buttons projected onto the assembly board.

Abstract: Control station which comprises: a seat (10) for the operator of the said control station, the seat (10) comprising at least one arm rest (30), and a control and command assembly, said assembly comprising a control stick (1) with controls, mechanical components for transmitting and generating forces and movement to and from the control stick (1), components (17) for measuring the position of the control stick (1), and electronic components which are connected to the control stick (1) and via which the control and command assembly is operated, the control stick (1) of the said control station being incorporated in the seat (10), the control stick (1) being situated moreover on the armrest (30).

Abstract: Pin bearing arrangement (10) for measuring loads in an aircraft landing gear (1), comprising a trailing arm (2), connected to at least one of the aircraft wheels (3), and a shock absorber (4), connected to the aircraft, whereby load (11) is transferred from the trailing arm (2) to the shock absorber (4), the trailing arm (2) being rotatable with respect to the shock absorber (4), the pin bearing arrangement (10) comprising at least one strain measuring element (12) attached to the pin bearing arrangement (10) in predetermined positions, these positions being selected such that the strain measuring element (12) gives at least a minimum detectable signal when the load (11) transferred is over a first threshold value, for any value of the angle (5) adopted by the trailing arm (2) with respect to the shock absorber (4).

Abstract: A tanker aircraft that comprises at least two hose (7) and drogue (9) refueling devices housed in gondolas (10) deployed under its wings comprising, in turn, at least one fuel pump (23) and winding drum (27) for hose (7), characterized in that said devices also comprise electric generator (21) actuated by wind turbine (11) that is connected to the electrical system of the tanker aircraft as an additional source for supplying power when the aircraft is in flight.

Abstract: A system for air to air refueling with an autonomous electrical system, comprising at least two hose and drogue devices (3, 5) housed in gondolas located underneath the wings of the aircraft, each refueling device comprising a plurality of components actuated by electrical actuators and its electrical system that is formed by two subsystems, each one of them comprising: a) Electric generator (11) actuated by a wind turbine (25) located in one of said gondolas; b) Energy storage device (19); c) Connection to the aircraft electrical system (15, 17); d) administrating device (21) equipped with means for ensuring the generation and storage of the energy required for responding to the electrical needs of the refueling system without recurring to the electrical system of the aircraft except in the event that the energy stored in said accumulation device (19) falls below a preset value.

Abstract: A method for controlling a boom (11) for in-flight refueling for increasing the damping of its displacement by means of a movement of control surfaces (16) related to its angular velocity, that comprises the following steps: a) At least two sensors (32, 33) are arranged in two sections of the boom (11) positioned on opposite sides of the valley (41) of the dominant flexible mode (40) for any length of its telescopic extension (12) and the moduli (D1, D2) of the angular deformations of the dominant flexible mode (40) are determined in them; b) The angular velocities (Q1, Q2) are obtained from the data supplied by said sensors (32, 33); c) The angular velocity Q unaffected by the resonance of the dominant flexible mode (40) is obtained as a function of said angular velocities (Q1, Q2) and said moduli (D1, D2), which eliminates the component of the elastic movement of the dominant flexible mode (40). The invention also relates to a control system and a computer program for executing said method.

Abstract: A method and device for in-flight including movable aerodynamic surfaces boom refueling operations using an articulated boom and a cable is disclosed.