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.
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.
H04B 1/38 - Transceivers, i.e. devices in which transmitter and receiver form a structural unit and in which at least one part is used for functions of transmitting and receiving
H04B 7/24 - Radio transmission systems, i.e. using radiation field for communication between two or more posts
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.
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.
G01R 31/02 - Testing of electric apparatus, lines, or components for short-circuits, discontinuities, leakage, or incorrect line connection
B60R 16/02 - Electric or fluid circuits specially adapted for vehicles and not otherwise provided forArrangement of elements of electric or fluid circuits specially adapted for vehicles and not otherwise provided for electric
G01R 31/04 - Testing connections, e.g. of plugs or non-disconnectable joints
H01R 43/28 - Apparatus or processes specially adapted for manufacturing, assembling, maintaining, or repairing of line connectors or current collectors or for joining electric conductors for wire processing before connecting to contact members, not provided for in groups
5.
SYSTEM FOR PERFORMING ELECTRICAL TESTS TO ELECTRICAL WIRING HARNESSES
The invention provides a system to perform tests quickly and accurately to wiring harness. The system comprises a workstation (15) equipped with an electrical test machine (12) with test terminals (19) disposed on the end of extendable hoses (17), a connection interface between harness connectors (13) and terminals tests (19), a working board (10) to perform on it the tests to a wiring harness (11), one or more projection devices (21, 21', 21") arranged to project images onto the working board (10) and a computer system (31) to supply such projection devices (21, 21', 21") with images (40) to assist the operators performing the tests. Said connection interface is formed by adapter modules (41) connectable by one side to the wiring harness connectors (13) and by the other to the test terminals (19). Test terminals (19) and adapter modules (41) comprise electronic circuits and external identification labels holding identification information.
An aircraft fuel system (100) comprises a fuselage tank (102) and wing fuel tanks (104, 106) each connected to the fuselage fuel tank by a respective fuel line (107, 109). A first fuel line (101) connects the fuselage fuel tank to a collector fuel tank (108), which is connected by second fuel lines (103A, 103B) to aircraft engines in use of the system. Unspent fuel output from the aircraft engines is returned to the collector fuel tank via third fuel lines (105A, 105B). A fuel line arrangement (111A, 111 B, 111C) is arranged to draw fuel from, and return that fuel to, the wing fuel tanks. Fuel within the third fuel lines is thermally coupled to fuel within the fuel line arrangement by a heat exchanger (110). Heat energy within unspent fuel output from the aircraft engines is transferred to the wing fuel tanks, reducing the likelihood of fuel freezing within these tanks during extended flying in cold environments.
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.
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.
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).
B29C 70/44 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
B29D 99/00 - Subject matter not provided for in other groups of this subclass
A digital audio system of an aircraft comprising one or more audio equipment (11) and one or more radio equipment (47) providing a reliable side tone to the operators. The audio equipment (11) and the radio equipment (47) have installed in the proximity, respectively, an audio-terminal (27) and a radio- terminal (45) connected to a digital network (15) including digital messages management units (37, 57) and digital signal processors (39, 59). The digital messages management unit (37) of the audio equipment (11) is provided with a computer program adapted to generate a side tone of an analog audio message issued by the microphone (21) of the audio equipment (11) and to activate/deactivate its sending to the headset (25) of the audio equipment (11) when the audio-terminal (27) receives from the radio-terminal (45) an activation/deactivation command for said side tone.
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.
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.
B64D 47/06 - Arrangements or adaptations of signal or lighting devices for indicating aircraft presence
G01R 31/00 - Arrangements for testing electric propertiesArrangements for locating electric faultsArrangements for electrical testing characterised by what is being tested not provided for elsewhere
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.
B23B 49/00 - Measuring or gauging equipment on boring machines for positioning or guiding the drillDevices for indicating failure of drills during boringCentring devices for holes to be bored
B23Q 17/00 - Arrangements for indicating or measuring on machine tools
14.
Workbench for manufacturing or checking electrical wiring harnesses
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.
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.
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.
The invention relates to a device for rendering electrical signals highly immune to noise. Specifically, the invention relates to a device for processing electrical signals (100) originating from a measurement sensor (60) that is subjected to noise disturbances owing to radio interferences and ray effects, such that said device uses a single current loop cable (70) through which the electrical signal (100) travels, coded according to the signal time (Ta) and the repetition time (Tr) of the current wave of said signal (100). In this way, the signal (100) contains an upper current state (10) and a lower current state (20) having values outside the decision window that activates a read device (4) in the device, which reads the electrical signal (100) originating from the sensor.
G01D 3/036 - Measuring arrangements with provision for the special purposes referred to in the subgroups of this group mitigating undesired influences, e.g. temperature, pressure on measuring arrangements themselves
18.
ACTIVE CONTROL PROCEDURES FOR THE CONNECTION OF VERY CAPACITIVE LOADS USING SSPCs.
Procedures for the connection of a very capacitive load (17) to a voltage bus (13) of an electric distribution system, by using a solid state power controller (SSPC) (15), where the current through the SSPC (15) is controlled actively by maintaining one of its parameters (the current and/or the derivative of the current) constant during the whole connection time (tc) of said very capacitive load (17) or during each one of a set of stretches of said connection time (tc). The invention also refers to SSPCs structured to carry out said procedures.
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′).
The invention relates to methods and systems for simulating the control panels of complex systems. The systems comprise a computer system suitable for simulating the operation of the control panels (11) by means of virtual panels (11') that include simulated control devices (31', 33', 35', 37', 39') of the control devices (31, 33, 35, 37, 39) of the control panels (11) implemented in display screens (10) that are connected to the components controlled by the control panels (11) or to a device for simulating these connections, such that the simulated control devices (31', 33', 35', 37', 39') of the virtual panels (11') are assigned signals or variables corresponding to the components that they control. The invention also relates to computer-implemented methods for the generation of the graphical interface (21) of said virtual panels (11').
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'").
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'").
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′″).
B60L 1/00 - Supplying electric power to auxiliary equipment of electrically-propelled vehicles
B60L 3/00 - Electric devices on electrically-propelled vehicles for safety purposesMonitoring operating variables, e.g. speed, deceleration or energy consumption
H02G 3/00 - Installations of electric cables or lines or protective tubing therefor in or on buildings, equivalent structures or vehicles
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 (1 1 ) 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 (1 1 ) 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). The invention also refers to a method for providing an indication of the on-ground condition of an aircraft, using a pin bearing arrangement (10) as the one described, and to a method for determining the positioning of the at least one strain measuring element (12) in such a pin bearing arrangement (10).
B64C 25/58 - Arrangements or adaptations of shock-absorbers or springs
G01G 19/07 - Weighing apparatus or methods adapted for special purposes not provided for in groups for weighing wheeled or rolling bodies, e.g. vehicles for weighing aircraft
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 (1 1 ) 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 (1 1 ) 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). The invention also refers to a method for providing an indication of the on-ground condition of an aircraft, using a pin bearing arrangement (10) as the one described, and to a method for determining the positioning of the at least one strain measuring element (12) in such a pin bearing arrangement (10).
B64C 25/58 - Arrangements or adaptations of shock-absorbers or springs
G01G 19/07 - Weighing apparatus or methods adapted for special purposes not provided for in groups for weighing wheeled or rolling bodies, e.g. vehicles for weighing aircraft
26.
SYSTEM FOR NIGHT VISION COMPRISING A LANTHANIDE DOPED CRYSTAL CONTAINING COATING AND AN INFRARED LASER ILLUMINATION MEANS
The invention relates to a night vision system for viewing selected objects, in order to provide improved night viewing of an object such as the refuelling device (21, 41) used in aerial refuelling operations between an aircraft tanker (11) and a receiver aircraft (13), rendering said object visible at night from an observation point, such as the receiver aircraft (13). The system comprises laser-based infrared lighting means (31) for illuminating the object and which are housed in the aircraft tanker (11) when the object to be viewed is the refuelling device (21, 41), one or more portions of the aforementioned object being coated with one or more coatings (51), each containing different concentrations of crystals doped with suitable lanthanides for upconverting the radiation emitted by an infrared laser light into visible light. The invention also relates to the coating (51) and to methods for producing same.
System for providing an enhanced night vision of a scene from an observation place, such as a system for providing an enhanced night vision of the scene (15) of an aerial refuelling operation of tanker aircraft (11), the system operating at night under low visibility conditions due to atmospheric disturbances such as fog, rain and particles in suspension, the system comprising: a) Laser-based infrared illumination means (33) of the scene, located in said observation place; b) A black-and-white high-definition imaging system comprising at least a high resolution camera (31) suitable for providing video signals of said scene when it is illuminated by said illumination means and at least a monitor for displaying images of said scene.
Support device (1) for probe (2) to measure the physical characteristics of air in contact with an aerodynamic surface (3) comprises: a rod (9) affixed to a probe (2) to distance probe (2) from an aerodynamic surface (3) such that probe (2) measures the air undisturbed by the aerodynamic surface (3); a support (4) adapted to be affixed to the aerodynamic surface (3) to which the foregoing rod (9) is connected such that support (4) permits rotation of rod (9) about the principal axis (12) of probe (9) to calibrate the position of probe (2) and such that the rotation of rod (9) may be locked once the position of probe (2) has been calibrated. An aerodynamic surface (3) comprising device (1), and a method for the calibration of probe (2) to measure the physical characteristics of the air in contact with an aerodynamic surface (3) are also disclosed.
G01L 27/00 - Testing or calibrating of apparatus for measuring fluid pressure
G01P 5/16 - Measuring speed of fluids, e.g. of air streamMeasuring speed of bodies relative to fluids, e.g. of ship, of aircraft by measuring differences of pressure in the fluid using Pitot tubes
System (10) for disconnecting the nozzle (1) of a boom from a receptacle (2) to which the nozzle (1) is connected for fuel transfer, comprising latches (3) which are situated in the nozzle (1) and engage with latch-pins (5) arranged in the said receptacle (2), characterized in that the system (10) comprises a receptacle disconnection system (20) which operates the latch-pins (5) of the receptacle (2) and a nozzle disconnection system (30) which operates the latches (3) of the nozzle (1) such that, when an operator performs normal disconnection of the nozzle (1), the system (10) sends a first signal (21) to the receptacle (2) so that its latch-pins (5) are retracted in order to release the latches (3) of the nozzle (1) and, in parallel, sends a second signal (31) to the nozzle (1) so that the latches (3) of the nozzle (1) are retracted and release the said nozzle (1).
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.
A telescoping tube (42) for fuel transfer operations, this tube (42) comprising a fixed part (41 ) and a moving part (40), such that this moving part (40) comprises in turn means for dynamic sealing (21 ) which guarantee the sealing of the moving part (40) against the fixed part (41 ), means of cushioning (22) which absorb the energy of the impact of the moving part (40) against the fixed part (41 ) in operations for extending and retracting the tube (42) and means of protection (23) against electrical discharges which earth the moving part (40) to the fixed part (41 ), the aforementioned means (21, 22 and 23) all being incorporated in a single unit in the moving part (40) of the telescoping tube (42), hence providing the aforementioned moving part (40) with all the aforementioned characteristics in a compact form, with the minimum weight and length. 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, which comprises a telescoping tube (42) with the abovementioned characteristics.
Control post that comprises: a seat (10) for the operator of said control post, the seat (10) comprising at least one armrest (30), and a control and command assembly, said assembly comprising a command lever (1) with controls, mechanical elements for the transmission and generation of forces and movement from and to the command lever (1), elements (17) for measuring the position of the command lever (1) and electronic elements connected to the command lever (1) whereby the control and command assembly operates; the command lever (1) of said control post being incorporated in the seat (10), the command lever (1) furthermore being located on the armrest (30).
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 (212) overlaid images under controlled depth order of a virtual apparatus, and real images of said device, and providing a simulated response to control means (210), based on data of the position and behavior of said device (205) and on data of the position and behavior of said virtual apparatus (209).
G06F 19/00 - Digital computing or data processing equipment or methods, specially adapted for specific applications (specially adapted for specific functions G06F 17/00;data processing systems or methods specially adapted for administrative, commercial, financial, managerial, supervisory or forecasting purposes G06Q;healthcare informatics G16H)
G09B 9/042 - Simulators for teaching or training purposes for teaching control of vehicles or other craft for teaching control of land vehicles providing simulation in a real vehicle
34.
Training method and system comprising mixed real and virtual images
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.
G09B 9/08 - Simulators for teaching or training purposes for teaching control of vehicles or other craft for teaching control of aircraft, e.g. Link trainer
G09B 9/042 - Simulators for teaching or training purposes for teaching control of vehicles or other craft for teaching control of land vehicles providing simulation in a real vehicle
G09B 9/05 - Simulators for teaching or training purposes for teaching control of vehicles or other craft for teaching control of land vehicles the view from a vehicle being simulated
A refueling apparatus for interconnecting a tanker aircraft (11) with a receiver aircraft in flight comprising a boom (21) joined to said tanker aircraft (11) by means of a mechanical articulation (41) having control means including a central computer station, an inner fuel conduit, a refueling nozzle (27) at its distal end and, and a smart tip assembly comprising a first module (83) having load sensing means, a second module (85) having load alleviation means and a third module (87), joined to the nozzle (27), having a mechanical fuse (99) for allowing the safe separation of tanker and receiver aircraft in the event of overloads. The invention also comprises a method of load alleviation for minimizing the loads on the boom (21).
Method and device for operations with an in-flight refuelling boom by means of the use of an articulated boom (11) and a cable (18), said boom (11) comprising movable aerodynamic surfaces (16) such that the method comprises the following steps: a) from the completely stowed and retracted position of the boom (11), the cable (18) begins to be paid out, and therefore the boom (11) starts to descend, said cable (18) being maintained under tension throughout step a) by means of the force provided by the movable aerodynamic surfaces (16) and/or the force of gravity on the boom (11); b) once the boom (11) is in its fully deployed position or the lower end of the flight container of the boom (11) has been reached, pay-out of the cable (18) stops; c) with the length of paid-out cable (18) remaining fixed, the boom (11) is placed in a position suitable for commencing the manoeuvres of refuelling the receiving aircraft; d) the manoeuvre of connecting the boom (11) to the receiving-aircraft receptacle is started, by means of controlling the movable aerodynamic surfaces (16); and e) once the connection has been made, fuel begins to be transferred to the receiving aircraft.
A method and device for in-flight including movable aerodynamic surfaces boom refueling operations using an articulated boom and a cable is disclosed. The method includes: (a) from a completely stowed-away and retracted position of the boom, the cable is initially released, thereby starting to lower the boom, such that the said cable is kept tensioned during the whole of step (a) by the force supplied by the movable aerodynamic surfaces and/or the force of gravity acting on the boom; (b) after reaching the maximum deployed position of the boom, or the bottom end of the flight envelope of the boom, release of the cable is stopped; (c) while keeping the length of released cable fixed, the boom is brought into a suitable position for commencing the maneuvers for refueling of the receiver aircraft; (d) the manoeuvre for connecting the boom to the receptacle of the receiver aircraft is started by control of the movable aerodynamic surfaces; and (e) once the connection has been established, the transfer of fuel to the receiver aircraft is started.
The invention relates to a system for illuminating an in-flight refueling operation involving a tanker aircraft (14) and a receiver aircraft (13), comprising: a generating device (2) for generating a light emission, substantially in a near infrared spectrum; a directing device (12) for directing the emission to define an emission envelope (15) containing a spatial range of in-flight refueling positions of the receiver aircraft (13) relative to the tanker aircraft (14); further comprising a collecting device (3) for collecting the light emission generated by the generating device (2) and means (5) for transmitting the light emission collected by the collecting device (3) to the directing device (12). The invention also relates to a method for illuminating an in-flight refueling operation involving a tanker aircraft (14) and a receiver aircraft (13), said method defining an emission envelope (15) which contains a spatial range of in-flight refueling positions of the receiver aircraft (13) relative to the tanker aircraft (14).
The invention relates to a system for lighting an in-flight refuelling operation involving a tanker aircraft (14) and a receiving aircraft (13), which system comprises: a generation device (2) for generating an emission of light substantially in a near infrared spectrum; a directing device (12) for directing the emission in order to define an emission envelope (15) containing a spatial field or domain of in-flight refuelling positions of the receiving aircraft (13) with respect to the tanker aircraft (14); and which additionally comprises a collecting device (3) for collecting the emission of light generated by the generation device (2), and means (5) for transmitting the emission of light collected by the collecting device (3) to the directing device (12). The invention also relates to a method for lighting an in-flight refuelling operation involving a tanker aircraft (14) and a receiving aircraft (13), such that said method defines an emission envelope (15) containing a spatial field of in-flight refuelling positions of the receiving aircraft (13) with respect to the tanker aircraft (14).
Aircraft command and control unit, in particular for flight control surfaces of an aircraft, and for controlling and commanding aircraft devices that require aerodynamic control, comprising: -actuating means for moving flight control surfaces; an automatic flight control system for the aircraft or aircraft device, connected to the actuating means for moving the flight control surfaces; and -at least one flight controller (1) on which the operator or pilot acts, and that receives a force (2) applied by the pilot, connected to the automatic flight control system and to the actuating means for moving the flight control surfaces, and that comprises: -means to generate force on the controller and -means to detect the position of the controller; the flight controller (1) also comprising: -means to detect the force (2) applied to the controller (1); and at least one control unit that receives information on the position of the controller (1) and the force (2) applied to the controller, sending this information to the means of generating force on the controller (1).
System (1) for providing indication of the position of a refuelling boom (2) in a tanker aircraft relative to a receptacle (17) in a receiver aircraft during refuelling operations, in particular in the approximation operation, the system (1) comprising a plurality of light emitting devices (23-33) mountable on the boom (2), each emitting device (23-33) providing a respective visible light beam, said light beams providing spots of incidence (3-13) when contacting the receptacle (17) in the receptor aircraft, in such a manner that the position of the spots of incidence (3-13) on the receptacle (17) varies depending on the position of the refuelling boom (2) relative to the receiver aircraft in the approximation operation. The invention also relates to a method for the approximation operation of a refuelling boom (2) in a tanker aircraft to a receptacle (17) in a receiver aircraft operating such a system (1).
Methods and systems for analysing sealing in fluid deposits, that include the following steps: a) injecting a tracer gas into the deposit at a predetermined pressure and temperature; b) capturing external images of the deposit using an IR camera in a predetermined zone of the spectral band in which said tracer gas is optically active; c) locating unintended holes in the deposit using gas leaks detected by displaying said images or images obtained from them. The systems include an IR camera fitted with a filter for capturing images of the outside of the deposit and a computer connected to it provided with a software program for displaying the images captured by the camera or processed images based on them. The invention also relates to a computer program for performing the method.
G01M 3/22 - Investigating fluid tightness of structures by using fluid or vacuum by detecting the presence of fluid at the leakage point using special tracer materials, e.g. dye, fluorescent material, radioactive material for pipes, cables, or tubesInvestigating fluid tightness of structures by using fluid or vacuum by detecting the presence of fluid at the leakage point using special tracer materials, e.g. dye, fluorescent material, radioactive material for pipe joints or sealsInvestigating fluid tightness of structures by using fluid or vacuum by detecting the presence of fluid at the leakage point using special tracer materials, e.g. dye, fluorescent material, radioactive material for valves
G01M 3/38 - Investigating fluid tightness of structures by using light
Device (3) for providing a warning signal when the inlet or suction cowling doors (8, 9) of an aircraft are not correctly fixed by primary locking means (6), such that said device (3) comprises a panel (4), the panel (4) being fixed using rotating means (5) arranged on one of the two suction cowling doors (8 or 9), such that the panel (4) closes into this same suction cowling door (8 or 9) when said rotating means (5) turn, thereby at least partially covering the primary locking means (6), such that all the primary locking means (6) must be properly fixed for the panel (4) to close, and the fact of at least one of the primary locking means (6) of the panel (4) not being properly fixed preventing the correct closure of the panel (4).
Device (3) for providing a warning signal when the fan cowl doors (8, 9) of an aircraft are not properly latched by primary locks (6), wherein the device comprises a panel (4) the panel (4) being rotatably mounted on one of the two fan cowl doors (8 or 9), the panel (4) being closed on that one fan cowl doors (8 or 9) by rotation thereby covering at least partially the primary locks (6), such that all the primary locks (6) have to be properly latched for the panel (4) to be closed, and at least one of the panel (4) primary locks (6) not being properly latched prevents proper closing of the panel (4).
The invention relates to a system for performing refuelling operations, for lifting and launching an in-flight aircraft refuelling arm (6) between a tanker aircraft and a receiver aircraft, including a linking device (5) which can be connected to the arm (6) and a lifting/lowering device (14) for operating the linking device (5) and, consequently, the arm (6), such that, during refuelling, the arm (6) is lowered using the lifting/lowering device (14). The aforementioned linking device (5) includes connection means (7) capable of: disconnecting the arm (6) from the linking device (5), thereby enabling a refuelling operation to be performed with the arm in free flight; and connecting the arm (6) to the linking device (5), thereby facilitating the lifting of the arm (6).
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.
G06F 19/00 - Digital computing or data processing equipment or methods, specially adapted for specific applications (specially adapted for specific functions G06F 17/00;data processing systems or methods specially adapted for administrative, commercial, financial, managerial, supervisory or forecasting purposes G06Q;healthcare informatics G16H)
47.
METHODS AND SYSTEMS FOR REDUCING THE STRUCTURAL COUPLING PHENOMENON IN SYSTEMS FOR CONTROLLING AN AIR REFUELLING BOOM
The invention relates to a method for controlling an air refuelling boom (11) in order to provide increased damping of the movement of the boom by moving control surfaces (16) as a function of the angular velocity thereof. The method comprises the following steps: a) placing at least two sensors (32, 33) in two sections of the boom (11), located on opposite sides of the valley (41) of the dominant flexible mode (40) for any length of the telescopic extension (12) thereof, and determining therein the moduli (D1, D2) of the angular deformations of the dominant flexible mode (40); b) obtaining the angular velocities (Q1, Q2) from the data provided by the sensors (32, 33); and c) obtaining the angular velocity Q not affected by the resonance of the dominant flexible mode (40) as a function of the angular velocities (Q1, Q2) and the moduli (D1, D2), which eliminates the elastic movement component from the dominant flexible mode (40). The invention also relates to a control system and a computer program for executing said method.
The invention relates to a modular device for removing and installing aircraft components comprising a modular frame (41) as main system of the device, common for every aircraft component which is to be installed or removed, this modular frame (41) being assembled in the front attaching points (2) and the rear attaching points (3) of the pylon lugs of the airframe, and this frame (41) comprising: a forward frame (7), at least two lateral frames (8) and a rear structure (9, 10). The invention also relates to a method for installing such a device for removing and installing aircraft components, and to a method for operating said device.
B64F 5/00 - Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided forHandling, transporting, testing or inspecting aircraft components, not otherwise provided for
The invention relates to a system (1) comprising double-walled ducts, suitable for transporting fluids to at least one other system. The system (1) includes an inner duct (3) for transporting the fluid and an outer duct (2) for transporting possible leaks in the system (1), as well as a clearance (8) between the two ducts (2, 3) and at least one elbow, plus at least one bushing (4, 5) which connects the system (1) at least to the other system, whereby said bushing (4, 5) can slide inside the system (1) before being connected to the system (1) and to other systems. In addition, the ends of the inner duct (3) can be connected to other systems and the outer duct (2) can be connected to one end of the bushing (4, 5), said bushing (4, 5) providing the closed structural integrity of the system (1). The invention also relates to a method for producing one such double-walled duct system.
The invention relates to a reinforcement device for lifting a retractable refuelling tube (11) interconnecting a feeder aircraft (13) and a receiver aircraft during flight, the retractable tube (11) being connected to the feeder aircraft (13) by means of a mechanical articulation (45) and a hoisting cable (23). Said device comprises a secondary cable (31) fixed to one end of the retractable tube (11), and fixed, on its other end, to a cable actuating device (41) arranged inside the feeder aircraft (13), said secondary cable (31) extending along the lower face of the feeder aircraft (13) and the retractable tube (11), and fixed to the feeder aircraft and the tube in at least three intermediate points by fixing means (34, 35, 36, 37) that can be released by a force exerted via the secondary cable (31). The cable actuating device (41) comprises reeling means (43, 45, 47, 49) for reeling the secondary cable (31) in such a way as to lift the retractable tube (11) into the retracted position.
The invention relates to a method for obtaining digital images during retractable tube operations for refuelling in the air, between a feeder aircraft and a receiver aircraft, said method comprising the following steps: black and white digital images of the receiver aircraft illuminated with IR light are captured at the same time as colour digital images of laser light points projected from the feeder aircraft over the receiver aircraft; said black and white digital images and said colour digital images are combined in order to obtain single images containing information in black and white and in colour; and the combined images are sent to a control station located in the feeder aircraft. The invention also relates to a device for obtaining digital images during retractable tube operations for refuelling in the air, between a feeder aircraft and a receiver aircraft, to be installed in the feeder aircraft.
The invention relates to a device for reducing the cross-stream force generated by an aircraft air refuelling boom (1), characterised in that it consists of at least one plate (31) having two cantilevered flanges (32, 33) which are provided with perforations (34) such that the dynamic pressure of the wake produced in the boom (11) is lower than that of the free stream.
Device to reduce the lateral force generated by an aerial refueling boom (11) of an aircraft characterized in that it has at least one plate (31), the plate (31) has two cantilevered wings (32, 33), the wings (32, 33) have perforations (34), so that the wake produced in the boom (11) has a lower dynamic pressure than that of the free stream.
An aircraft telescopic in-flight refueling mast comprising a metallic structural beam (31), electrically connected to the aircraft by flexible conductive means (33), having inside a fixed metallic tube (11) and a metallic telescopic tube (11) providing the fuel conduit, and, attached to said beam (31), flight control surfaces (41) and protection means against electric discharges, specially lightning strikes and electro-static discharges, including insulated means (39, 51) and low conductive means (15, 17) for reducing the lightning currents at a safe level and for draining the static charge created during the refueling, and conductive means (19, 21, 23, 33, 43) providing a safe lightning current path and good electrical bonding for electro-static discharge.
H01H 47/00 - Circuit arrangements not adapted to a particular application of the relay and designed to obtain desired operating characteristics or to provide energising current
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