Abstract: A system for monitoring the state of a two-part-cowl lock unit, the lock unit comprising a pair hook-keeper, has a rod mechanically connected to the lock unit, a spring mechanically coupled with the rod, and a warning mechanism configured to be activated by the rod, to warn of the state of the two-part-cowl lock unit. An aircraft may also be configured to include at least one of the systems for monitoring the state of a two-part cowl lock.

Abstract: A method for in-flight refueling of a receiver aircraft from a tanker aircraft including: measuring continuously a tension at an end of a hose extending from the tanker aircraft towards the receiver aircraft, and using the measured tension to control a torque applied to a drum device deploying the hose from the tanker aircraft such that the tension at the end of the hose conforms to target tensions during each phase of the refueling operation.

Abstract: The present disclosure refers an aerial refueling coupling for in-flight parameter measuring, including a body configured to receive and support a probe and a removable shell that covers at least part of the body. The aerial refueling coupling includes a sensor system for detecting at least one parameter related to in-flight refueling operation, a data processing device configured to provide a measure at least relative to parameters detected by the sensor system, a portable storage system, and a power supply system comprising at least on battery for supplying energy, and a ram air turbine for their activation when the aerial refueling coupling is in-flight. The data processing device, the storage system and the power supply system are mounted onto the body covered by the shell.

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: A system to perform tests quickly and accurately to wiring harnesses. The system comprises a workstation equipped with an electrical test machine with test terminals disposed on the end of extendable hoses, a connection interface between harness connectors and terminals tests, a working board to perform on it the tests to a wiring harness, one or more projection devices arranged to project images onto the working board and a computer system to supply such projection devices with images to assist the operators performing the tests. The connection interface is formed by adapter modules connectable by one side to the wiring harness connectors and by the other to the test terminals. Test terminals and adapter modules comprise electronic circuits and external identification labels holding identification information.

Abstract: The present invention refers to a dual pressure regulation system to ensure a proper pressure regulation during the Aerial REFUELING operations with Hose and Drogue systems. More specifically is directed to dual redundant fuel pressure regulation systems. The pressure regulator system comprises two pressure regulators (10, 20) located in series and a control element (30) for controlling the movement of both regulators operatively connected downstream (34) the second pressure regulator (20) such that the movement of the pressure regulators (10, 20) is independently controlled by the control element (30) according to the delivery pressure downstream the second regulator (20).

Abstract: A digital audio system of an aircraft comprising one or more pieces of audio equipment and one or more pieces of radio equipment providing a reliable side tone to the operators. The audio equipment and the radio equipment have installed in the proximity, respectively, an audio-terminal and a radio-terminal connected to a digital network including digital messages management units and digital signal processors. The digital messages management unit of the audio equipment is provided with a computer program adapted to generate a side tone of an analog audio message issued by the microphone of the audio equipment and to activate/deactivate its sending to the headset of the audio equipment when the audio-terminal receives from the radio-terminal an activation/deactivation command for said side tone.

Abstract: The invention provides in-flight refueling systems with a communication sub-system available in radio silence operations including at least a first digital wireless data link comprising a first RF transceiver and a second RF transceiver coupled, respectively, to first and second antennas located in two points inside the boom or the hose of the refueling system or in RF communication with them and connected, respectively, to refueling control units in the tanker aircraft and in the free end of the refueling device by data buses allowing a digital communication between them.

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: An indication system and method for detecting and displaying the relative position during fuel transfer. The system comprises a first input device configured to be capable of detecting the extended length from the tanker aircraft of elongated hose and to be capable of sending the detected length of elongated hose to the control module. The control module is operably connected to a display and configured to be capable of receiving an input signal from the input device of hose extension, transforming it into a corresponding output signal of the position of the receiver aircraft inside a refueling range of limit positions and sending the corresponding output signal to the display, which is configured to be capable of displaying information indicating the position of the receiver aircraft inside the refueling range of limit positions.

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 system for detecting the status of a tube for fuel transfer. It includes a nozzle for a telescoping tube employed in air to air refueling and transfer of fuel on a tanker aircraft with a system that detects the status of the connection of the nozzle with respect of a receptacle in a receiving aircraft, the system detecting the characteristics of the status of the connection of the nozzle in the receptacle by direct measurement of parameters in the nozzle itself of the tanker aircraft.

Abstract: Transmission of data and audio messages between tanker and receiver aircrafts to facilitate air refueling operations using a boom device, wherein the method includes transmitting a data message from one aircraft to the other aircraft as an analog signal via the electro-magnetic connection which is also used for transmission of audio messages between the aircrafts which may be operating in a radio silence environment.

Abstract: A guidance apparatus mounted on the belly of a tanker aircraft for providing visual indications to the pilot of the receptor aircraft with respect to the approaching operation to carry out the refueling by means of a refueling boom. The guidance apparatus includes light emitting devices including modules of light emitting diodes and control devices for supplying current to the light emitting diodes that include dimming control units for controlling the intensity of the light emitted by the light emitting devices via a dimming signal depending on a dimming voltage. The dimming control units are adapted to provide to the light emitting devices a pulse-exponential amplitude modulated dimming signal so that the light intensity can be properly controlled in all visibility conditions.

Abstract: The present invention refers to a dual pressure regulation system to ensure a proper pressure regulation during the Aerial REFUELING operations with Hose and Drogue systems. More specifically is directed to dual redundant fuel pressure regulation systems. The pressure regulator system comprises two pressure regulators (10, 20) located in series and a control element (30) for controlling the movement of both regulators operatively connected downstream (34) the second pressure regulator (20) such that the movement of the pressure regulators (10, 20) is independently controlled by the control element (30) according to the delivery pressure downstream the second regulator (20).

Abstract: A control system and method of the anti-skid computers of an aircraft are provided. The control system comprises two IMA computers, comprising each one an Avionics Computer Control Device, an Avionics Computer Monitoring Device and at least one dual data acquisition means and at least one dual processing means. Each Avionics Computer Control Device and each Avionics Computer Monitoring Device are connected to the anti-skid computers of both sides.

Abstract: Training method for the simulation of an operation performed by at least one device which is part of a real apparatus, wherein the method comprises providing to display means overlaid images under controlled depth order of a virtual apparatus, and real images of said device, and providing a simulated response to control means, based on data of the position and behavior of said device and on data of the position and behavior of said virtual apparatus.

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 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: Simulation system for a control center of a complex system such as an aircraft (23) made up of one or more control panels (11) with a set of control devices (31, 33, 35, 37, 39) for components of said complex system, comprising a suitable computer system for the simulation of the operation of said control panels (11) by using virtual panels (11?) which include simulated control devices (31?, 33?, 35?, 37?, 39?), implemented in screens (10) which are connected to the components controlled by said control panels (11), or to a simulating device for said connections, so that the signals or variables corresponding to the controlled components are assigned to their corresponding simulated control devices (31?, 33?, 35?, 37?, 39?) in the virtual panels (11?). The invention also refers to a computer-implemented method for the generation of the graphic interface (21) said virtual panels (11?).