A method for manufacturing a structural component is disclosed. The structural component comprises a skin formed by layers of composite material, stringers made of a composite material fixed to the skin and ribs made of a composite material fixed to the skin, the structural component has sub-panels joined to one another and each comprising a sub-skin defined by first layers of composite material, at least one stringer and at least one rib fixed to an internal surface of the sub-skin, wherein the structural component comprises a continuous sub-wall defined by the union of the external surfaces of the sub-skins of the sub-panels joined to one another, second layers of composite material are laminated on the first layers so as to define a continuous external over-skin layered on said sub-wall, wherein the skin is defined by the set of said sub-skins and over-skins and consists of the first and second layers.
B29C 70/68 - Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts by incorporating or moulding on preformed parts, e.g. inserts or layers
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
B29C 70/84 - Moulding material on preformed parts to be joined
2.
DATA PROCESSING SYSTEM AND METHOD FOR THE INTEGRATION OF A SIMULATION MODULE AND AN ON-BOARD MODULE
A data processing system (10) comprises: an on-board module (E-1,.„, E-n) configured to be boarded on a vehicle and to operate on board the vehicle; a simulation module (S-1,..., S- n) configured to simulate the behavior of a component of the vehicle; and an integration unit (16) configured to enable communication between the on-board module and the simulation module. The simulation module is configured to process signals (SS-1, SS-n) having a first format and the on-board module is configured to process signals (SH-1, SH-n) having a second format different from the first format. The integration unit is configured to: receive a first signal processed by the simulation module and having the first format; convert the first format into the second format, generating in response a second signal having the second format; and provide the second signal to the on-board module; and/ or receive a third signal processed by the on-board module and having the second format; convert the second format into the first format, generating in response a fourth signal having the first format; and provide the fourth signal to the simulation module.
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
Multi-target tracking software loadable in and executable by electronic processing resources comprising at least one quantum computer. The multi-target tracking software is designed to cause, when executed, the electronic processing resources to become configured to receive unlabelled data indicative of positions of targets, in particular vehicles, to be tracked; the unlabelled data failing to be indicative of the identities of the targets. In addition, the multi-target tracking software is designed to cause, when executed, the electronic processing resources to become configured to compute candidate tracks, that may possibly be followed by the targets, based on the received unlabelled data; and to compute an initial quantum state representative of said candidate tracks. The multi-target tracking software is further designed to cause, when executed, the electronic processing resources to become configured to compute, by means of a quantum optimization model, a final quantum state representative of final tracks.
G01S 7/41 - Details of systems according to groups , , of systems according to group using analysis of echo signal for target characterisationTarget signatureTarget cross-section
G06N 10/20 - Models of quantum computing, e.g. quantum circuits or universal quantum computers
G06N 10/40 - Physical realisations or architectures of quantum processors or components for manipulating qubits, e.g. qubit coupling or qubit control
5.
SYSTEM FOR DECOUPLING A CARRIER FOR A PIECE OF AMMUNITION OF A FIREARM
System for decoupling a carrier for a piece of ammunition (42) of a firearm, comprising: a carrier recuperator (60), including: a first and a second cylinder (111, 112) respectively comprising a first and a second piston (63, 67); wherein each piston (63, 67) defines, in the respective cylinder (111, 112), a primary chamber (16, 66) full of liquid, and the two primary chambers (16, 66) are in fluidic communication with each other to allow a flow of liquid; the second piston (67) defines, in the second cylinder (112), a secondary chamber (68) containing a return medium for moving the second piston (67) and pumping the liquid into the primary chamber (16) of the first cylinder (111). The system includes a carrier rearming transmission, comprising: a first and a second articulated connecting rod (142, 143) hinged to a fulcrum (158), wherein the first connecting rod (142) is also hinged to a recoiling mass (8) of a firearm; a straight guide (137, 138) whereon the articulated connecting rods (142, 143) are intended to abut and slide; a rearming lever (93) freely rotatable about a first axis of rotation (153), and having a slider (154) at a first end thereof; a slotted link lever (62) rotatable about a second axis of rotation (21), and having a guide in which the slider (154) of the rearming lever (93) is slidably mounted, wherein the first piston (63) is connected to the slotted link lever (62) in such a way as to constrain the motion of the first piston (63) to the rotation of the slotted link lever (62); a crank lever (144, 148), rotatable about the first axis of rotation (153), having a first end connected to the recoiling mass through the two articulated connecting rods (142, 143), and configured to interfere with the rotation of the rearming lever (93); a release transmission configured to guide the movement of the carrier (114) and to selectively hold in position and release the rearming lever (93); wherein the first piston (63) is connected to the release transmission in such a way as to constrain the motion of the first piston (63) to a movement of the carrier (114).
F41A 9/06 - Feeding of unbelted ammunition using cyclically moving conveyors, i.e. conveyors having ammunition pusher or carrier elements which are emptied or disengaged from the ammunition during the return stroke
F41A 9/16 - Movable ammunition carriers or loading trays, e.g. for feeding from magazines pivoting or swinging in a vertical plane parallel to the barrel axis
Ice detection system (2) for control surfaces (S) of aircraft (A) whereon a layer (L) of water and/or ice may be present. The system comprises: a support structure (20); a fist sensor (3) of the capacitive type, adapted to detect the electrical properties of the layer (L) of water and/or ice; and a second sensor (4) of the ultrasonic type, adapted to detect the mechanical properties of the layer (L) of water and/or ice. The second sensor (4) comprises: an ultrasonic transceiver (41) adapted to generate ultrasonic waves to be transmitted, and to receive the ultrasonic waves reflected by the layer (L) of water and/or ice on the surface (S); a delay line (42), arranged between the ultrasonic transceiver (41) and the surface (S), through which the transmitted and reflected ultrasonic waves are propagated. The delay line (42), which extends along an axis (X), comprises a first line (42A) and a second line (42B) parallel or coaxial to each other. The length of the first line (42A) along said axis (X) is greater than that of the second line (42B), resulting in at least two different reflected ultrasonic waves. The sensors (3, 4) are arranged in the support structure (20), thus defining a compact single measurement system.
Fire interference device (3) for a firearm (1), adapted to prevent movements of a safety element (22) in order to prevent the release of a blowback mass (21); comprising: a fixed portion (31), adapted to be mounted on a cradle (12), comprising: an electro-hydraulic actuator (32); a control unit (30), adapted to control the electro-hydraulic actuator (32); a cylindrical cam (33), whereupon the actuator (32) acts, adapted to assume a raised configuration and a lowered configuration; and a movable portion (34), adapted to be mounted on a breech ring (13), comprising: a first lever (35) comprising: a horizontal arm (351), adapted to be operated by the cylindrical cam (33); and a vertical arm (352), adapted to engage the safety element (22); and a retaining lever (36) adapted to lock the first lever (35). The retaining lever (36) is adapted to allow the safety element (22) to snap only when the horizontal arm (351) is engaged by the cylindrical cam (33) in the lowered configuration and the retaining lever (36) is clear of the cylindrical cam (33).
F41A 17/64 - Firing-pin safeties, i.e. means for preventing movement of slidably-mounted strikers
F41A 3/10 - Block action, i.e. the main breech opening movement being transverse to the barrel axis with sliding breech-block, e.g. vertically
F41A 25/00 - Gun mountings permitting recoil or return to battery, e.g. gun cradlesBarrel buffers or brakes
F41A 19/36 - Mechanical firing mechanisms having only slidably-mounted striker elements, i.e. percussion or firing pins the percussion or firing pin being movable relative to the breech-block propelled by a spring under tension in block-action guns
A Radio Frequency System-on-Chip, RFSoC, (12) for a radar system (10), the RFSoC (12) comprising a Programmable Logic, PL, module (30) and a Processing System, PS, module (32), operatively coupled to each other, the PS module (32) being configured to perform PS operations and the PL module (30) being configured to perform PL operations, the PL module (30) comprising at least: a Radio Frequency Data Converter, RFDC, module (36) configured to perform RFDC operations of said PL operations; a Digital Beam Forming, DBF, module (38) configured to perform DBF operations of said PL operations; and a Digital Pulse Compression, DPC, module (40) configured to perform DPC operations of said PL operations, the PS module (32) comprising at least: a Timing and Antenna Control, TAC, module (42) configured to perform TAC operations of said PS operations; a Signal Processor for Tactical Multi-Mission Radar, SPT, module (44) configured to perform SPT operations of said PS operations; a Message and Data Handler, MDH, module (46) configured to perform MDH operations of said PS operations; and an Enhanced Tracker, ETRK, module (48) configured to perform ETRK operations of said PS operations, and the RFSoC (12) being configured to receive a radar signal indicative of at least one target object (50) to be detected and to detect the at least one target object (50) by processing the radar signal through the PL module (30) and the PS module (32).
A series of convertible aircrafts with a core with an airframe defining a first axis is described; a first, a second, a third, a fourth, a fifth and a sixth rotor which are rotatable about respective first, second, third, fourth, fifth and sixth axis, and operable independently of each other so as to generate respectively a first, a second, a third, a fourth, a fifth and a sixth thrust value independent of each other; the core comprises an electric power source and electric motors which are connected to said first, second, third, fourth, fifth and sixth rotor; each aircraft of the series comprises a module associated with a respective architecture and interfaced with said core.
A composite material, in particular for aeronautical applications, comprising: a first pre-impregnated layer having a resin-based matrix reinforced with fibres to give the first layer predefined mechanical properties; and a second layer of magnetic field intensifier material, superimposed on a face of the first layer and joined to the first layer along that face; the second layer comprises electrically conductive fibres, preferably of carbon, dispersed in the second layer in at least two directions with different orientations and having equivalent electrical resistivity, parallel to the aforementioned face, of less than 600 μΩm, preferably less than 200 μΩm and even more preferably less than 100 μΩm, so as to facilitate localized heating by electromagnetic induction; the first and second layers joined together define a lamina of super-weldable composite material.
A process for manufacturing a structural component made of composite material comprising a skin and at least one stiffening stringer applied rigidly and integrally to one face of the skin. The process comprises a) arranging, on a tool, a plurality of first layers of uncured or pre-cured composite material, forming the stringer and having a raised portion protruding from at least one flange; b) arranging, on the tool, a plurality of second layers of uncured or pre-cured composite material forming the skin; c) making a face of the skin and the flange of the stringer adhere to each other; d) applying a predetermined temperature and pressure on the assembly to compact the layers together, possibly curing the uncured material and rigidly joining the skin to the stringer; and e) performing a cutting operation on the free end side edge/s of the flange in a slanted direction.
B29C 70/30 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or coreShaping by spray-up, i.e. spraying of fibres on a mould, former or core
B29C 70/54 - Component parts, details or accessoriesAuxiliary operations
B29C 70/88 - Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts characterised primarily by possessing specific properties, e.g. electrically conductive or locally reinforced
B29D 99/00 - Subject matter not provided for in other groups of this subclass
B64F 5/10 - Manufacturing or assembling aircraft, e.g. jigs therefor
13.
COHERENT BEAM COMBINATION SYSTEM AND METHOD FOR CONTROLLING AN OUTPUT BEAM
INININININtbtxYZZ) of the movable optical sensor (23) based on the output-beam control signal; and provide, based on the detection signal (INT), a plurality of phase control signals (U) to the phase modulators (42) of the plurality of channels, so as to optimize the intensity of the sampled beam.
H01S 3/00 - Lasers, i.e. devices using stimulated emission of electromagnetic radiation in the infrared, visible or ultraviolet wave range
H01S 3/13 - Stabilisation of laser output parameters, e.g. frequency or amplitude
H01S 3/23 - Arrangement of two or more lasers not provided for in groups , e.g. tandem arrangement of separate active media
H01S 3/10 - Controlling the intensity, frequency, phase, polarisation or direction of the emitted radiation, e.g. switching, gating, modulating or demodulating
G02B 26/08 - Optical devices or arrangements for the control of light using movable or deformable optical elements for controlling the direction of light
An avionic display software for an aircraft comprising: a display device coupled to receive image rendering display commands and responsively display rendered images; a terrain data source to output terrain data representative of terrain in a field of view of a pilot of the aircraft; an avionic flight data source to output avionic data representative of an avionic state of the aircraft, including a roll angle thereof; and computing resources coupled to the terrain data source to receive terrain data therefrom, to the avionic flight data source to receive avionic data therefrom, and to the display device to supply image rendering display commands thereto based on the received terrain and avionic data. The avionic display software is executable by the computing resources to cause, when executed, the computing resources to become programmed to cause rendered images representative of an out-the-window view of the operator of the aircraft to be displayed by the display device. A rendered image comprises one or both of rendered terrain and rendered sky, which are representative of real-world terrain and sky outside of the aircraft and whose positions and orientations are dependent upon position and orientation of the aircraft relative thereto. A rendered image further comprises a rendered sky veil. The sky veil is an overlapping graphic representation rendered at least partially transparent in such a manner that portions of the rendered sky veil that overlap with the rendered sky are not discernable from the rendered sky, and the rendered terrain is viewable through transparent portions of the sky veil that overlap with the rendered terrain. The sky veil is rendered as a band stationary in the rendered image during roll of the aircraft. The sky veil is rendered at least partially transparent along its width such that a width of a transparent region of the sky veil depends on a roll angle of the aircraft.
A method for estimating rotor torques of an aircraft capable of hovering and comprising a plurality of rotors, which are rotatable under the action of respective rotor torques; and an engine, which is operatively connected to the rotors to provide them with an engine torque. Each rotor comprises a hub and a plurality of blades articulated on the respective hub in such a way that respective collective pitch angles are adjustable. The method comprises the steps of i) calculating a symmetric component on the basis of the engine torque; ii) receiving a signal associated with collective pitch angles; iii) calculating an asymmetric component on the basis of a pitch angle difference between the collective pitch angles; and iv) calculating each rotor torque as the algebraic sum of the symmetric component and the respective asymmetric component.
09 - Scientific and electric apparatus and instruments
12 - Land, air and water vehicles; parts of land vehicles
13 - Firearms; explosives
14 - Precious metals and their alloys; jewelry; time-keeping instruments
25 - Clothing; footwear; headgear
28 - Games; toys; sports equipment
Goods & Services
Guidance systems for missiles; flight simulators for
aircraft; aircraft control software; simulation software;
virtual reality software; radar apparatus; headgear being
protective helmets; spectacles; sunglasses; covers for cell
phones and tablet computers. Military aircraft; military drones. Aerial targets for military use; missiles; launchers for
missiles; rocket launching military vehicles. Necklaces (jewellery); medals; pins (jewellery); jewellery;
time instruments. Clothing; flying suits; neck scarves (mufflers); footwear;
bathing suits; headgear, t-shirts. Drones (toys); scale model aeroplanes; playing cards; games.
17.
CONTROL UNIT AND INDICATOR FOR AN AIRCRAFT CAPABLE OF HOVERING OR FOR A FLIGHT SIMULATION SYSTEM OF SAID AIRCRAFT, AND RELATIVE METHOD FOR ASSISTING THE PERFORMANCE OF A MANOEUVRE
A control unit for an aircraft capable of hovering or for a flight simulation system of the aircraft is described; the control unit is programmed to:
receive in input a plurality of data associated with equipment and/or kits actually installed or simulated on the aircraft and/or with the operating configuration of the equipment and/or kits; the equipment and/or kits causing a reduction of the actual or simulated forward velocity of the aircraft;
store a table defining a correspondence between each datum and a respective value of a first signal associated with a value of maximum forward velocity of the aircraft; and
display the lowest of the first signals.
Test device for an aeronautical component (2) wherein M low-energy impacts are performed on the component to be subjected to testing (2) by calculating the relative uncertainty Ui of the non-destructive tests. A destructive test (block 120) is performed on the aeronautical component (2) by measuring and storing the value of a quantity VI representative of the elastic stress applied to the component during the destructive test and based on this the uncertainty of the destructive test is calculated (block 130). The absolute value of the difference between target values of quantities Ci based on a theoretical model that describes the elastic behaviour of the component to be subjected to testing and the value of the quantity VI representative of the elastic stress applied to the component during the destructive test (ABS (Ci-Vi)) is compared with the product of the uncertainty of the destructive test AI and a scaling factor k in order to certify the theoretical model as describing with sufficient accuracy the behaviour of the aeronautical component during the destructive test.
CONTROL UNIT AND INDICATOR FOR AN AIRCRAFT CAPABLE OF HOVERING OR FOR A FLIGHT SIMULATION SYSTEM OF SAID AIRCRAFT, AND RELATIVE METHOD FOR ASSISTING THE PERFORMANCE OF A MANOEUVRE
A control unit for an aircraft capable of hovering or for a flight simulation system of the aircraft is described, the control unit is programmed to receive at input at least a first signal associated with real or simulated flight parameters of the aircraft and to provide at output a second signal associated with a forward velocity to never exceed of the aircraft; the control unit is programmed to process a third signal associated with an actual or simulated weight of the aircraft; to associate plurality of tables to respective intervals of values of the third signal; each table associating a plurality of values of the second signal with a respective first signal; and to process the second signal, based on the table associated with the relative interval of the third signal and the respective first signals.
Display system for a vehicle operable by a user, the display system comprising: a graphics generator configured to acquire input safety critical data indicative of one or more operative parameters of the vehicle and generate, based on the input safety critical data, an intermediate video frame signal indicative of an intermediate video frame, wherein the intermediate video frame comprises a first frame region that is a visual representation of monitoring safety critical data and that includes encoding markers uniquely associated to the monitoring safety critical data, wherein the monitoring safety critical data and the input safety critical data reciprocally correspond in a condition of correct working of the graphics generator and do not reciprocally correspond in a condition of incorrect working of the graphics generator; a display control unit coupled to the graphics generator and configured to receive the intermediate video frame signal and determine the monitoring safety critical data based on the encoding markers; a display monitoring unit coupled to the display control unit and configured to receive both the input safety critical data and the monitoring safety critical data determined from the encoding markers, reciprocally compare the input safety critical data and the monitoring safety critical data and generate a command signal based on said comparison, the command signal being indicative of the correspondence, or of the lack of correspondence, between the input safety critical data and the monitoring safety critical data, wherein the display control unit is further configured to receive the command signal and, based on the command signal and the intermediate video frame and if the input safety critical data and the monitoring safety critical data correspond, generate a confirmed video frame signal indicative of a confirmed video frame that is configured to be displayed to the user and that is a visual representation of the monitoring safety critical data.
B64D 43/00 - Arrangements or adaptations of instruments
G01C 23/00 - Combined instruments indicating more than one navigational value, e.g. for aircraftCombined measuring devices for measuring two or more variables of movement, e.g. distance, speed or acceleration
G06F 3/147 - Digital output to display device using display panels
21.
METHOD FOR CLASSIFYING THE MANOEUVRES PERFORMED BY AN AIRCRAFT BY SEGMENTATION OF TIME SERIES OF MEASUREMENTS ACQUIRED DURING A FLIGHT OF THE AIRCRAFT
A computer-implemented method for classifying manoeuvres performed by an aircraft, including: acquiring a data structure including at least one unknown data matrix including a plurality of time series of samples of quantities related to the flight of the aircraft, the samples being relative to a succession of instants of time; applying to the unknown data matrix a neural network generating a corresponding probability matrix including, for each instant of time of the succession of instants of time, a corresponding probability vector including, for each class of a plurality of classes of manoeuvres, a corresponding estimate of the probability that, in the instant of time, the aircraft has performed a manoeuvre belonging to the class; and selecting, for each instant of time of the succession of instants of time, a corresponding class of manoeuvres, based on the probability estimates of the corresponding probability vector.
The coherent beam recombination system provides an output recombined beam and comprises: a laser source providing a source beam with linewidth; a beam broadener providing a broadened beam from the source beam; a splitter splitting the broadened beam into a plurality of secondary beams; a plurality of channels coupled to the splitter. Each channel receives a respective secondary beam and provides a respective intermediate beam. Each channel has an optical amplifier, a phase modulator, an optical delay line, and an opto-mechanical element. The CBC system further comprises an optical sensor that provides a detection signal indicative of an intensity of a received optical beam; a focusing optics that receives the intermediate beams, provides the output recombined beam from a first portion of each intermediate beam, and provides a sampled recombined beam to the optical sensor from a second portion of each intermediate beam. The CBC system further comprises a control unit coupled to the optical sensor and the plurality of channels. The control unit comprises a phase-locking module configured to: provide a plurality of phase control signals to the phase modulators; receive the detection signal from the optical sensor, indicative of an intensity of the sampled recombined beam; calculate a cost function from the detection signal, wherein the cost function is a function of the intensity of the sampled recombined beam; perform an optimization algorithm of the cost function, configured to maximise the intensity of the sample recombined beam; and provide a plurality of updated phase control signals, based on a result of the optimization algorithm.
The invention relates to an automated system for transporting and/or sorting objects (3) comprising : automated means of transport (1) that include transport units (2) designed to transport objects (3); a handling system (4) equipped with a gripping system (5) and operable to load objects (31) onto the automated means of transport (1); and electronic processing and control means configured to receive data relating to the position and speed of the transport units (2) and data indicative of the geometric characteristics and/or dimensions of the objects (3) transported, process the data received and control the operation of the handling (4) and gripping (5) systems on the basis of the processed data. The processing and control means, in order to load a first given object (31) on a first predetermined transport unit (21), are programmed to: determine a first trajectory to be executed by the handling system (4) over N first objects (3) transported by the transport units (2) to reach said first predetermined transport unit (21), wherein N is an integer greater than zero; determine a first maximum height between the heights of the N first objects (3); control the handling system (4) and the gripping system (5) so that they execute the first trajectory holding the first given object (31) at a height such that a lower surface of said first given object (31) remains above said first determined maximum height and, upon reaching the first predetermined transport unit (21), place the first given object (31) on said first predetermined transport unit (21).
G05B 19/418 - Total factory control, i.e. centrally controlling a plurality of machines, e.g. direct or distributed numerical control [DNC], flexible manufacturing systems [FMS], integrated manufacturing systems [IMS] or computer integrated manufacturing [CIM]
A transmission assembly (3; 3'; 3''; 3'''; 3''''; 3'''''; 3''''''; 3'''''''; 3'''''''') for an aircraft (1; 1'; 1''; 1'''; 1''''; 1'''''; 1''''''; 1'''''''; 1''''''''), comprising a member to be lubricated (18; 40; 1800; 1801; 1400; 1401) for transmission of the motion; a tank (50; 500''; 500'''; 500''''; 500'''''; 500''''''; 1500; 2500) for a lubricating fluid and passive retaining means (60; 60'; 501''; 503''', 504'''; 503''''; 503''''', 506'''''; 600''''''; 1600; 2600) adapted to prevent, in use, outflow of the lubricating fluid from the tank (50; 500''; 500'''; 500''''; 500'''''; 500''''''; 1500; 2500) when the temperature of the member to be lubricated (18; 40; 1800; 1801; 1400; 1401) is below a threshold value and to allow, in use, outflow of the lubricating fluid from the tank (50; 500''; 500'''; 500''''; 500'''''; 500''''''; 1500; 2500) towards said member to be lubricated (18; 40; 1800; 1801; 1400; 1401), when the temperature of the member to be lubricated (18; 40; 1800; 1801; 1400; 1401) is higher than or equal to the threshold value.
The present invention concerns a connection group (1) including a first connector (2) and a second connector (3) designed to be coupled with each other. The connection group (1) includes also a first bushing (4) rotatably mounted on the first connector (2) by means of a first retaining ring (5), whereby the first bushing (4) is rotatable around a longitudinal axis of the first connector (2). Said first bushing (4) comprises internal teeth mutually arranged according to a given angular configuration. The second connector (3) is equipped with a second bushing (6) that is fixedly mounted on said second connector (3) by means of a second retaining ring (7) and through an internal groove profile, whereby the second connector (3) and the second bushing (6) are fixed to each other; said second bushing (6) having external slots arranged according to the given angular configuration, whereby said external slots of the second bushing (6) correspond to the internal teeth of the first bushing (4). The first connector (2) and the second bushing (6) are designed to be inserted, respectively, in the second connector (3) and the first bushing (4). The first bushing (4) is designed to be rotated around the longitudinal axis, thereby rotating also the second bushing (6) and the second connector (3) that is screwed around the first connector (2), whereby complete connection/coupling of the first and second connectors (2, 3) is achieved. The first and the second bushings are marked with one and the same graphical symbol and/or one and the same respective color.
H01R 13/645 - Means for preventing, inhibiting or avoiding incorrect coupling by exchangeable elements on case or base
H01R 24/40 - Two-part coupling devices, or either of their cooperating parts, characterised by their overall structure having concentrically or coaxially arranged contacts specially adapted for high frequency
The present invention concerns a projection-based display system (1) including: a light source (2) that is a light engine based on a RGB microled array, a coupling optics (3) and a diffractive waveguide (4) that comprises a dark, reflective rear face and a transparent front face (4a); wherein the light source (2) is configured to inject one or more light beams/signals carrying one or more given images into the diffractive waveguide (4) via the coupling optics (3), whereby the injected light beams/signals impinge on the dark, reflective rear face, the given image(s) are focused on said dark, reflective rear face, and said injected light beams/signals are reflected by said dark, reflective rear face thus reaching the transparent front face (4a) where said given image(s) is/are displayed.
Method implemented by computer for detecting flight regimes of an aircraft equipped with a monitoring system that acquires samples of quantities relative to the flight including: acquiring an unknown matrix including, for each quantity, a corresponding series of samples; performing smoothing operations of each series of samples, so as to generate a corresponding series of smoothed samples and determining a corresponding approximating function defined by a respective series of coefficients and by a plurality of base functions, the smoothed series of samples forming a smoothed unknown matrix; on the basis of the base functions, applying to the smoothed unknown matrix and to the corresponding sets of coefficients a classifier trained to generate, for each flight regime among a plurality of flight regimes, a corresponding estimate of the probability that the smoothed unknown matrix and the corresponding sets of coefficients belong to a cluster relative to the flight regime; identifying a flight regime in which the aircraft operated, on the basis of the estimates generated by the classifier.
1n1m1m1p1nj1m1m1p1j1j1m1m1pp) into the arrangements that can be assumed along the guide path (112). An input interface device (210) is configured to be operated by an operator in order to receive control information. A control system (208) is configured for controlling the moving system (114) as a function of the detections of the sensors (200, 202, 204) and of the displacement transducer (206), and as a function of the control information supplied by the input interface device (210).
Testing apparatus (10) for testing a bird strike on an aircraft part (P), comprising: a hollow, rectilinear duct (12) along a longitudinal direction (x) to accommodate coaxially therein a cylindrical bolt (D) with a metal casing to be accelerated for the test simulating a bird strike; a plurality of accelerating devices (14), arranged on the duct (12) in consecutive positions along the longitudinal direction (x), each adapted, when activated, to exert an electromagnetic force on the bolt (D) to accelerate it in the longitudinal direction (x); an electronic control unit (16); and a speed sensor (18), to measure the speed of the bolt (D) along the longitudinal direction (x), after it has been accelerated by all the accelerating devices (14), wherein the electronic control unit (16) is configured to control the activation of each of the accelerating devices (14), based on the measurement signal received by the speed sensor (18).
Control software (1) of an industrial robot (2) loadable into, and executable by, computing resources of the industrial robot (2) so that, when executed, the industrial robot (2) becomes configured to carry out operations on real pieces in a work environment. The control software (1) is designed so that, when executed, the industrial robot (2) becomes configured to receive operation instructions to be carried out in the work environment and containing spatial coordinates, expressed in a virtual reference system, of a virtual environment modelling of the work environment and to carry out the operations instructed. In addition, the control software (1) is designed so that, when executed, the industrial robot (2) becomes configured to calculate a spatial transformation model (16) to align the virtual reference system of the work environment, in the virtual environment modelling, with a real reference system of the work environment in which the industrial robot (2) operates, in order to allow the latter to carry out the operations in the work area based on instructions received. In order to calculate (block 15) the spatial transformation model (16) between the virtual reference system and the real reference system, the control software (1) is also designed so that, when executed, the industrial robot (2) becomes configured to cause (block 4) a contact feeler (3) of the industrial robot (2) to interact with a real piece (18) in the work area to determine, in the real reference system, spatial coordinates of a number of contact points of surfaces of the real piece (18) at alignment holes made in the real piece (18) and determine (block 10) the spatial coordinates of at least one characteristic point, in particular the centre, of each alignment hole (17) based on the spatial coordinates of one or more of the contact points relative to the alignment hole (17). The control software (1) is also designed so that, when executed, the industrial robot (2) becomes configured to calculate (block 15) the spatial transformation model (16) between the virtual reference system and the real reference system based on the spatial coordinates of the at least one characteristic point of each alignment hole (17) and the spatial coordinates of the characteristic point of a corresponding alignment hole (17) in the virtual environment modelling of the real piece (18).
09 - Scientific and electric apparatus and instruments
12 - Land, air and water vehicles; parts of land vehicles
25 - Clothing; footwear; headgear
28 - Games; toys; sports equipment
Goods & Services
Electrical and electronic equipment and instruments for
aircraft and helicopters, namely, flight control system,
beacon control panel, anemometer, helicopter pilot control
panel, fuel control panel, engine control panel, gyro
compass control panel, electronic flight display, engine and
crew warning system, aircraft engine and flight system
monitors; flight simulator; avionics sensor systems, namely,
navigation systems for use in aircraft and helicopters;
communication transmission apparatus, namely, antennas,
wireless transmitters and receivers for use on aircraft and
helicopters; aircraft and helicopter testing apparatus and
instruments, namely, general caution indicator (master
caution) and general warning indicator (master warning) for
use on aircraft and helicopters; computer hardware for use
in aircraft and helicopters; computer software for flight
command and control and navigation for use on aircraft and
helicopters; electronic publications, namely, electronic
books, magazines, brochures, electronic magazines (e-zines),
manuals in the aviation sector and helicopter, downloadable
or recorded on magnetic, optical and electronic media; smart
watches. Aircraft; helicopters. Clothing; shirts; trousers; pants; sweaters; scarves; flight
jackets; wind jackets; rainwear; footwear; headgear; hats;
caps. Toys; scale model aircraft; scale model helicopter; toy
construction block kits; toy aircraft construction block
kits; toy helicopters construction block kits; scale model
airports; pilot toys; aviator toys; helicopter pilot toys;
puzzles; aircraft puzzles; helicopter puzzles;
radio-controlled toy aircraft; radio-controlled toy
helicopters; games; board games; strategy games; rescue
games; card games; aircraft games; helicopter games;
electronic games; video game apparatus; video game consoles;
consoles for playing video games in the field of aircraft;
consoles for playing video games in the field of
helicopters.
09 - Scientific and electric apparatus and instruments
12 - Land, air and water vehicles; parts of land vehicles
25 - Clothing; footwear; headgear
28 - Games; toys; sports equipment
Goods & Services
Electrical and electronic equipment and instruments for
aircraft and helicopters, namely, flight control system,
beacon control panel, anemometer, helicopter pilot control
panel, fuel control panel, engine control panel, gyro
compass control panel, electronic flight display, engine and
crew warning system, aircraft engine and flight system
monitors; flight simulator; avionics sensor systems, namely,
navigation systems for use in aircraft and helicopters;
communication transmission apparatus, namely, antennas,
wireless transmitters and receivers for use on aircraft and
helicopters; aircraft and helicopter testing apparatus and
instruments, namely, general caution indicator (master
caution) and general warning indicator (master warning) for
use on aircraft and helicopters; computer hardware for use
in aircraft and helicopters; computer software for flight
command and control and navigation for use on aircraft and
helicopters; electronic publications, namely, electronic
books, magazines, brochures, electronic magazines (e-zines),
manuals in the aviation sector and helicopter, downloadable
or recorded on magnetic, optical and electronic media; smart
watches. Aircraft; helicopters. Clothing; shirts; trousers; pants; sweaters; scarves; flight
jackets; wind jackets; rainwear; footwear; headgear; hats;
caps. Toys; scale model aircraft; scale model helicopter; toy
construction block kits; toy aircraft construction block
kits; toy helicopter construction block kits; scale model
airports; pilot toys; aviator toys; helicopter pilot toys;
puzzles; aircraft puzzles; helicopter puzzles;
radio-controlled toy aircraft; radio-controlled toy
helicopters; games; board games; strategy games; rescue
games; card games; aircraft games; helicopter games;
electronic games; video game apparatus; video game consoles;
consoles for playing video games in the field of aircraft;
consoles for playing video games in the field of
helicopters.
An aircraft window configured to reduce the intensity of vibrations transmitted from outside the aircraft to inside the aircraft cabin comprising: a first element of transparent material (2) arranged, in use, facing the outside of the aircraft; a second element of transparent material (3) arranged, in use, facing the cabin; a gap (4) that separates the first and second elements of transparent material-(2,3) which are arranged facing and spaced apart from one another, a first transparent sheet element (5) applied to a first face of the first element (2) facing the gap; and at least one second transparent sheet element-(7) applied to a second face of the second element-(3) facing the gap. The first and second transparent sheet elements (5,7) are made of transparent viscoelastic material.
B64C 1/14 - WindowsDoorsHatch covers or access panelsSurrounding frame structuresCanopiesWindscreens
B32B 17/10 - Layered products essentially comprising sheet glass, or fibres of glass, slag or the like comprising glass as the main or only constituent of a layer, next to another layer of a specific substance of synthetic resin
B32B 27/08 - Layered products essentially comprising synthetic resin as the main or only constituent of a layer next to another layer of a specific substance of synthetic resin of a different kind
An articulated transmission joint (20; 20'; 20'') for connecting a control shaft (10) to a hub (15) of a rotor (8, 8', 8''), comprising: a first element (45, 45', 45'') rotatable about a first axis (C); a second element (50, 51, 52; 50'', 51'', 52'') rotatable about a second axis (D); and connecting means (60, 60', 60'') to allow transmitting the motion between the first and the second element (45, 45', 45''; 50, 51, 52; 50'', 51'', 52'') of a torque having a main component along the first axis (C) and a torque having a main component along the second axis (D); the connecting means (60, 60', 60'') comprise, a roller (54) articulated on the first element (45, 45', 45''); and a chamber (53) defined at least partially by the second element (50, 51, 52; 50'', 51'', 52'') and housing at least partially the roller (54); the chamber (53) is delimited towards the roller (54) by a first surface (59) that contacts the roller (54) circumferentially to the first axis (C), after the rotation of the first element (45) about the first axis (C); the first and second element (45, 45', 45''; 50, 51, 52; 50'', 51'', 52'') are coupled so as to allow a tilt of an angle (α) between the first and second axis (C, D).
F16D 3/205 - Universal joints in which flexibility is produced by means of pivots or sliding or rolling connecting parts one coupling part entering a sleeve of the other coupling part and connected thereto by sliding or rolling members one coupling part having radially projecting pins, e.g. tripod joints the pins extending radially outwardly from the coupling part
B64C 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
F16D 3/202 - Universal joints in which flexibility is produced by means of pivots or sliding or rolling connecting parts one coupling part entering a sleeve of the other coupling part and connected thereto by sliding or rolling members one coupling part having radially projecting pins, e.g. tripod joints
09 - Scientific and electric apparatus and instruments
12 - Land, air and water vehicles; parts of land vehicles
13 - Firearms; explosives
14 - Precious metals and their alloys; jewelry; time-keeping instruments
25 - Clothing; footwear; headgear
28 - Games; toys; sports equipment
Goods & Services
Guidance systems for missiles; flight simulators for
aircraft; aircraft control software; simulation software;
virtual reality software; radar apparatus; headgear being
protective helmets; spectacles; sunglasses; covers for cell
phones and tablet computers. Military aircraft; military drones. Aerial targets for military use; missiles; launchers for
missiles; rocket launching military vehicles. Necklaces (jewellery); medals; pins (jewellery); jewellery;
time instruments. Clothing; flying suits; neck scarves (mufflers); footwear;
bathing suits; headgear, t-shirts. Drones (toys); scale model aeroplanes; playing cards; games.
36.
METHOD FOR MANUFACTURING A BOX-SHAPED STRUCTURE IN COMPOSITE MATERIAL FOR AIRCRAFT
A method for manufacturing a box-shaped structure for aircraft, wherein the structure longitudinally extends between a first axial end and a second axial end and has a first longitudinal wall; a second longitudinal wall; a plurality of spars longitudinally extending between said first wall and second wall; a reinforcing rib transversal to the spars and inserted, between the first and second wall, in the area of a transversal sector interposed between the first axial end and the second axial end; the second wall comprises a main portion and a closing portion, which are coplanar to one another and define two distinct pieces with discontinuity and separated in the area of the transversal sector, so as to facilitate the insertion of the reinforcing rib without jeopardizing the structural properties of the box-shaped structure.
B29D 99/00 - Subject matter not provided for in other groups of this subclass
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
B29K 277/00 - Use of polyamides, e.g. polyesteramides, as reinforcement
B29L 31/30 - Vehicles, e.g. ships or aircraft, or body parts thereof
B32B 3/08 - Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by features of form at particular places, e.g. in edge regions characterised by added members at particular parts
B32B 5/02 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by structural features of a layer comprising fibres or filaments
B32B 5/26 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by the presence of two or more layers which comprise fibres, filaments, granules, or powder, or are foamed or specifically porous one layer being a fibrous or filamentary layer another layer also being fibrous or filamentary
A method for manufacturing a box-shaped structure for aircrafts, the structure extending along a longitudinal direction between a first longitudinal end and a second longitudinal end, and comprising: a first longitudinal wall; a second longitudinal wall facing the first wall and spaced from the first wall by a non-zero amount; a plurality of spars extending longitudinally and between said first wall and second wall; and at least one reinforcing rib arranged transversal to the spars at a transversal sector interposed between the first and the second longitudinal end; each spar has a spar cavity defining a lack of material extending longitudinally from an axial coordinate, which corresponds to the transversal sector, up to the second longitudinal end, so that the reinforcing rib can be easily inserted even after the integral coupling between the first wall, the second wall and the spars without compromising the structural properties of the box-shaped structure.
An avionics system (1) comprising electronic processing resources (2) including a multicore processor (3) with a plurality of cores (4), on each of which one or more software applications may be stored and executed, and a cache memory (5) organised in cache lines (12); a system memory (7) organised in memory banks (13); and a system bus (9) though which the multicore processor (3) can access the system memory (7). The memory banks (13) comprise unshared memory banks (13a) assigned to the cores (4) of the multicore processor (3) for the performance of the respective software application(s). The unshared memory banks (13a) are partitioned among the cores (4) of the multicore processor (3) such that each unshared memory bank (13a) is exclusively assigned to, and accessible by, one core (4) only, whereby each core (4) is assigned to, and can access, one or more unshared memory banks (13a) which are different from those assigned to, and accessible by, the other cores (4). The memory banks (13) further comprise shared memory banks (13b) shared among the cores (4) of the multicore processor (3) for sharing data among the software applications executed by the cores (4). Each shared memory bank (13b) comprises a row buffer (14) acting as a cache within the shared memory bank (13b) and an associated row semaphore (20) selectively settable to cause the associated row buffer (14) to be writable by a data-producer software application that needs to write data in the row buffer (14) and to prevent it from being readable by data-consumer software applications during writing of the row buffer (14), and, respectively, to be readable by a single or different data-consumer software applications that need to read data from the row buffer (14).
G06F 13/16 - Handling requests for interconnection or transfer for access to memory bus
G06F 13/28 - Handling requests for interconnection or transfer for access to input/output bus using burst mode transfer, e.g. direct memory access, cycle steal
G06F 13/368 - Handling requests for interconnection or transfer for access to common bus or bus system with decentralised access control
39.
TAIL ASSEMBLY FOR A GUIDED AND FIN-STABILIZED PROJECTILE
The tail assembly (10) comprises a fixed part (12) to be connected to the back of a main body (2) of a projectile (1), and defining a longitudinal axis (X-X). There is a movable part (14) equipped with a plurality of stabilizing fins (16) and mounted to the back of the fixed part (12), freely rotatable relative thereto about the longitudinal axis (X-X). The movable part (14) is axially movable relative to the fixed part (12) between : an abutment condition, wherein the fixed part (12) and the movable part (14) are in axial abutment with each other; and a spaced-apart condition, wherein the fixed part (12) and the movable part (14) are axially spaced apart, thus defining a perimetral gap (G) in between. There is also an elastic group (18) tending to retain the movable part (12) in the spaced-apart condition.
The magazine (100) comprises a frame (102) configured for internally housing a plurality of pieces of ammunition (A) and comprising a guide structure (110) which defines a guide path (112) and which is configured to allow the pieces of ammunition (A) to slide laterally along the guide path (112). A moving system (114) comprises a movable chain structure (120) which can be moved supported by the frame (102) and which is configured for carrying and laterally pushing the pieces of ammunition (A). The guide structure (110) is configured to be crossed by an axially intermediate portion of each one of the pieces of ammunition (A). The movable chain structure (120) is configured for receiving each one of the pieces of ammunition (A) and comprises a pair of chains (122-b) supported by the frame (102). A plurality of rod members (124) connect the chains (122a-b) in the axial direction and axially cross the guide structure (110) at the guide path (112). The chains (122a-b) are configured for axially holding, between themselves, each one of the pieces of ammunition (A). Each pair of successive rod members (124) is configured for laterally holding, on opposite sides, each one of the pieces of ammunition (A).
An underwater acoustic imaging system (1), designed to be coupled to a water vehicle (100), is provided with: an acoustic imaging device (2), to acquire three-dimensional acoustic images of a water volume; a mechanical movement module (3), coupled to the acoustic imaging device (2) to cause underwater movement thereof; and an electronic unit (4) coupled to the acoustic imaging device (2) and to the mechanical movement module (3). The electronic unit (4) controls the mechanical movement module (3) to implement two distinct operating phases of the acoustic imaging device (2), cooperating to generate a continuous stream of said three-dimensional acoustic images: a searching phase, in which the acoustic imaging device (2) is designed to be held substantially still and is configured to perform a scan as a result of a movement of the water vehicle (100); and an in-depth analysis phase, in which the acoustic imaging device (2) is designed to be driven in a scanning movement by the mechanical movement module (3) for an in-depth analysis of an element of interest identified in the water volume.
A system for generating light radiation to neutralize microorganisms comprises a light source for emitting a light radiation, storage means with one or more unique identification codes, each of which is associated with a respective microorganism, and at least one respective wavelength range associated with said microorganism, and a logic control unit. The logic control unit is configured to select a wavelength range based on the microorganism to be neutralized, activate the light source in such a way that light radiation emitted by said light source has a wavelength within said selected wavelength range, so that, when the system is in use, the light radiation induces optical resonance in the microorganism, causing denaturation of genetic patrimony of the microorganism.
Fire fighting drone comprising an exoskeleton defining an internal space extending along an axis H and a flexible bag stably housed in the internal space, provided with a release valve and configured to contain a fire fighting liquid; a support structure provided with a plurality of thrusters adapted to perform a thrust that enables the support structure to be supported in flight; the support structure is connected to a first end portion of the exoskeleton; a plurality of movable directional wings carried by the exoskeleton, extending outwards from the exoskeleton itself and angularly movable relative to the exoskeleton around respective axes H transverse to the axis H; an electronic control unit adapted to control the thruster, to generate the release signal and adapted to control the actuators that perform the rotation of the wings; the electronic control unit is configured to control said wings to allow the rotation of the wings during the free-fall phase of said drone which is released from an aircraft and thereby performs a certain trajectory of said drone from the aircraft to a launch zone; the electronic unit is configured to enable the discharge of said liquid from said bag and the activation of the thrusters following the discharge of the liquid to enable the flight of the support structure and of the exoskeleton containing the empty bag to a landing zone.
A62C 3/02 - Fire prevention, containment or extinguishing specially adapted for particular objects or places for area conflagrations, e.g. forest fires, subterranean fires
B64U 70/20 - Launching, take-off or landing arrangements for releasing or capturing UAVs in flight by another aircraft
B64U 101/47 - UAVs specially adapted for particular uses or applications for releasing liquids or powders in-flight, e.g. crop-dusting for fire fighting
44.
MAGAZINE FOR AN ARTILLERY INSTALLATION, PROVIDED WITH A MOVING SYSTEM
The magazine (100) comprises a frame (102) configured for internally housing a plurality of pieces of ammunition (A). The frame (102) comprises an inlet (103) configured for receiving the pieces of ammunition (A) and an outlet (105) configured for feeding such pieces of ammunition (A) to a weapon assembly (18). There is a guide structure (110) which extends between the inlet (103) and the outlet (105) to define a guide path (112), and which is configured to allow the pieces of ammunition (A) to slide laterally along the guide path (112). A moving system (114) comprises a movable chain structure (120), which can be moved supported by the frame (102), and which is configured for carrying and laterally pushing the pieces of ammunition (A) along the guide path (112). A motor (117) is configured for generating mechanical power, and a transmission mechanism (119) is configured to be driven by the motor (117) so as to move the movable chain structure (120) along the guide path (112) in a forward travel direction (J) and a backward travel direction (K), opposite each other.
limlimlim), an inhibition circuit (27) is activated, which brings the torpedo into a safety state in which the explosive warhead is prevented from exploding.
A locking device for an aircraft is described, comprising a body adapted to be fixed to a support surface, a first ring and a second ring rotatable the one with respect to the other with respect to a rotation axis between a first angular position and a second angular position. The first and second ring enclose an area for the landing of the aircraft and are contained within the body. The locking device also comprises a plurality of cables, which connect the first ring to the second ring. The locking device is positionable in an unlocking position, wherein the first and second ring are in the first angular position, the cables are spaced from said area; or in a locking position, wherein the first and second ring are in the second angular position and the cables occupy a region of the area, so as to cooperate in contact with the aircraft to constrain it with respect to the support surface.
The illumination optical device comprises a collimator, a light source, and an aperture. The collimator comprises a primary mirror, a secondary mirror, a tertiary mirror and a quaternary mirror mutually tilted so as to form a collimator optical path extending between the light source and the aperture and formed, in succession, by the light source, the quaternary mirror, the tertiary mirror, the secondary mirror, the primary mirror and the aperture. The light source is configured to emit light rays, along respective directions, which form a main beam propagating along directions intercepting the quaternary mirror so as to follow the collimator optical path; and a secondary beam propagating along directions not intercepting the quaternary mirror. The illumination optical device is characterised in that the collimator comprises a shielding structure configured to prevent illumination of the aperture by the secondary light beam.
A method to manufacture a structural component in composite material reinforced with stiffening stringers and comprising a skin and plurality of stringers having a hollow section fixed to said skin. The method comprising: a) laminating a plurality of first layers of composite material onto an external surface of a cure tool, b) laminating pluralities of second layers of composite material on longitudinal hollow expandable inserts, c) positioning each reinforcing element on a face of a second skin, d) holding each reinforcing element on the face of the second skin; e) housing the tool, skin and reinforcing elements inside a vacuum bag; and f) compacting together the first layers forming the skin with the second layers forming the stringers; g) housing skin and reinforcing elements in a further vacuum bag; and h) sealing the further vacuum bag; and i) applying preset temperature and pressure to the outside of the vacuum chamber.
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
B29C 70/54 - Component parts, details or accessoriesAuxiliary operations
B64C 1/00 - FuselagesConstructional features common to fuselages, wings, stabilising surfaces or the like
motmot of the measured current is lower than the first current threshold Imot-low or higher than the second current threshold, the generation and/or transmission of the activation command to the detonator (10) or the arrangement of the three components in the arming position is inhibited.
F42B 15/20 - Missiles having a trajectory beginning below water surface
F42C 11/04 - Electric fuzes with current induction
F42B 19/24 - Propulsion specially adapted for torpedoes by electric motors
F42B 19/30 - Propulsion specially adapted for torpedoes with timing control of propulsion
F42C 15/18 - Arming-means in fuzesSafety means for preventing premature detonation of fuzes or charges wherein a carrier for an element of the pyrotechnic or explosive train is moved
F42C 15/40 - Arming-means in fuzesSafety means for preventing premature detonation of fuzes or charges wherein the safety or arming action is effected electrically
F42C 15/44 - Arrangements for disarming, or for rendering harmless, fuzes after arming, e.g. after launch
50.
AIRCRAFT CAPABLE OF HOVERING AND METHOD FOR TRANSPORTING A LOAD SUSPENDED FROM SUCH AIRCRAFT
There is described an aircraft configured to be able to hover, comprising a fuselage; and a support element adapted to support a load, made of elastically deformable material and constrained to said fuselage; the support element being movable in an operating position in which it is arranged at least partially outside said fuselage and supports said load; the aircraft comprises a sock surrounding the support element arranged in said operating position; the sock is configured to contain the elastic return of the support element, in case the support element arranged in said operating position is sheared off.
The installation includes a traversing portion configured to be rotatably mounted and supported on a stationary support structure, to rotate about a traversing axis. An elevating portion is rotatably supported by the traversing portion about an elevating axis perpendicular to the traversing axis. A firearm assembly supported by the elevating portion has a barrel configured to fire linkless ammunitions through firearm assembly. A magazine is configured to contain a plurality of linkless ammunitions to be fed to the barrel. A feeding assembly is configured to transfer the linkless ammunitions from the magazine to the barrel. The magazine is carried by the traversing portion and is operatively integral therewith. The feeding assembly is carried by the elevating portion and is operatively integral therewith. A transfer device mounted on the traversing portion is configured to transfer the linkless ammunitions (A) from the magazine to the feeding assembly.
The invention concerns a multimode feed for a reflector antenna of a monopulse tracking system. The feed comprises: a receiving element having an aperture, which receives an electromagnetic wave and generates, from the electromagnetic wave, a waveguide signal comprising a plurality of higher-order modes, as a function of an incidence angle of the electromagnetic wave on the aperture; and a waveguide structure, coupled to the receiving element, which generates, from the plurality of higher-order modes, a first error signal at a first output port and a second error signal at a second output port. The waveguide structure has: a first coupler that extracts, from the waveguide signal, a first higher-order mode and provides a first extracted signal; a second coupler that extracts, from the waveguide signal, a second higher-order mode and provides a second extracted signal; a third coupler that extracts, from the waveguide signal, a third higher-order mode and provides a third extracted signal; a fourth coupler that extracts, from the waveguide signal, a fourth higher-order mode and provides a fourth extracted signal; a first summing element that sums the first extracted signal and the second extracted signal, thereby generating the first error signal at the first output port; and a second summing element that sums the third extracted signal and the fourth extracted signal, thereby generating the second error signal at the second output port.
A series of convertible aircraft with a core with an airframe defining a first axis is described; a first, a second, a third, a fourth, a fifth and a sixth rotor which are rotatable about respective first, second, third, fourth, fifth and sixth axis, and operable independently of each other so as to generate respectively a first, a second, a third, a fourth, a fifth and a sixth thrust value independent of each other; the core comprises first and second portions of respective half-wings and aerodynamic surfaces and each module comprises third and fourth portions of respective half-wings and aerodynamic surfaces.
B64U 50/19 - Propulsion using electrically powered motors
B64U 101/61 - UAVs specially adapted for particular uses or applications for transporting passengersUAVs specially adapted for particular uses or applications for transporting goods other than weapons for transporting passengers
B64U 101/64 - UAVs specially adapted for particular uses or applications for transporting passengersUAVs specially adapted for particular uses or applications for transporting goods other than weapons for parcel delivery or retrieval
An anti-torque rotor includes a mast rotatable about a first axis; a plurality of blades; an element slidable along the first axis, rotating integrally with the mast and operatively connected to the blades. The rotor also has a slidable control rod; a first bearing with a rotatable first ring, a second ring radially internal to the first ring and a plurality of first rolling bodies; a third ring slidable along the first axis and angularly fixed with respect to the first axis; and a locking element arranged in a first configuration, in which it prevents the relative rotation of the second and third rings and is movable from the first configuration to at least one emergency configuration, in which it renders the second ring free to rotate with respect to the third ring, when the first bearing is in a failure condition.
B64C 27/82 - RotorcraftRotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting-rotor torque or changing direction of rotorcraft
B64C 27/59 - Transmitting means, e.g. interrelated with initiating means or means acting on blades mechanical
A convertible aircraft with an airframe defining a first longitudinal axis is described; a pair of half-wings; a first, a second, a third, a fourth, a fifth and a sixth rotor rotatable about respective first, second, third, fourth, fifth and sixth axis, and operable independently of each other so as to generate respectively a first, a second, a third, a fourth, a fifth and a sixth thrust value independent of each other; said fifth and sixth rotor being carried by respective said half-wings and inclinable with respect to said airframe; the aircraft being switchable between a first hovering flight configuration wherein the sixth and seventh axis are arranged orthogonal to the first axis; and a second forward flight configuration wherein the sixth and seventh axis are arranged parallel to or inclined with respect to the first axis; the aircraft comprises first supports adapted to support the fifth and sixth rotor with respect to the respective half-wings; the first supports being arranged spaced apart from respective free ends of respective half-wings according to an extension direction of respective half-wings.
B64C 27/28 - Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with forward-propulsion propellers pivotable to act as lifting rotors
B64C 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
An anti-torque rotor includes a mast rotatable about a first axis; a plurality of blades; an element slidable along the first axis, rotating integrally with the mast and operatively connected to the blades. The rotor also has a slidable control rod; a first bearing with a rotatable first ring, a second ring radially internal to the first ring and a plurality of first rolling bodies; a third ring slidable along the first axis and angularly fixed with respect to the first axis; and a locking element arranged in a first configuration, in which it prevents the relative rotation of the second and third rings and is movable from the first configuration to at least one emergency configuration, in which it renders the second ring free to rotate with respect to the third ring, when the first bearing is in a failure condition.
B64C 27/82 - RotorcraftRotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting-rotor torque or changing direction of rotorcraft
B64C 27/59 - Transmitting means, e.g. interrelated with initiating means or means acting on blades mechanical
Method implemented through a computer for determining a maintenance plan of a group of aircraft, comprising receiving a data structure with a plurality of groups of values associated with a plurality of flights of the aircraft, wherein each flight has a duration, each group of values relates to a physical quantity associated with the use of an aircraft, and wherein each group of values is acquired during a flight by a detection system coupled to an aircraft. The method further comprises identifying one or more representative flights from the plurality of flights, starting from the data structure and using at least one statistical test, wherein the groups of values associated with the representative flights are, from a statistical viewpoint, values of typical use of the group of aircraft; determining a load sequence comprising the groups of values associated with the representative flights repeated a number of times, as a function of the duration of the respective representative flight; and determining a state of use of the group of aircraft, starting from the load sequence.
Communication system, comprising: a first data bus configured to transport a first data signal according to a first transmission direction; a second data bus configured to transport a second data signal according to a second transmission direction different from the first transmission direction; a synchronization bus; and a plurality of local resources generating a respective local signal to be transmitted on the first and second data bus. All transceivers are modulated with CDMA encoding and take place following a synchronism signal. The unidirectionality of transmission on the data buses guarantees the absence of interference. The communication system is fully scalable.
Device for controlling a cursor of a graphical user interface of a flight unit, comprising a base structure; a graspable body shaped to be grasped by a hand of an operator and movable with respect to the base structure by the manual force provided by the operator by means of his/her hand; a force sensor coupled to the graspable body and designed to sense the movements of the graspable body with respect to the base structure along at least a first axis and a second axis; an interface circuit for converting the signals provided by the force sensor into control signal of the graphical user interface of the flight unit in order to move the cursor along a first axis and a second axis of the graphical user interface based on the force provided to the graspable body by the operator.
G06F 3/0338 - Pointing devices displaced or positioned by the userAccessories therefor with detection of limited linear or angular displacement of an operating part of the device from a neutral position, e.g. isotonic or isometric joysticks
B64D 43/00 - Arrangements or adaptations of instruments
G06F 3/02 - Input arrangements using manually operated switches, e.g. using keyboards or dials
G06F 3/038 - Control and interface arrangements therefor, e.g. drivers or device-embedded control circuitry
62.
METHOD AND SYSTEM FOR DETECTING ANOMALIES RELATING TO COMPONENTS OF A TRANSMISSION SYSTEM OF AN AIRCRAFT, IN PARTICULAR A HELICOPTER
A computer-implemented method is described for detecting anomalies in a transmission system of an aircraft equipped with a monitoring system, which includes a number of sensors coupled to the transmission system and determines, for each flight of the aircraft a number of respective time intervals and acquires through each sensor, for each of the time intervals, a corresponding primary signal indicative of a corresponding dynamic quantity dependent on the operation of the transmission system during at least part of the time interval. For each sensor, the monitoring system determines, starting from each primary signal acquired through the sensor during a corresponding time interval, a corresponding set of values of at least one corresponding group of synthetic indexes. The method includes detecting anomalies of the transmission system on the basis of the groups of synthetic indexes.
An aircraft is provided that has a moving system for moving, during flight, sensors of the aircraft between a rest position in which the sensors are arranged within the aircraft, and a work position in which the sensors face directly, along a sensing direction, towards outside of the aircraft and towards the ground when the aircraft is in flight. The moving system has a frame arranged inside the aircraft, a slide supporting the sensors, and a pair of guides, each guide having a rail part supported on the frame, and at least one draw part arranged telescopically slidable relative to the relevant rail part along a direction of movement perpendicular to the sensing direction. The slide, mounted integrally with the draw parts of the pair of guides, slides along the direction of movement internally within the aircraft to move the sensors between the rest and work positions.
Method implemented by computer (16) for detecting a damage to a component (1), including: applying (212) a first neural network (40) to at least one multispectral image (25) of the component (1), formed by a plurality of images (30) of the component (1) in corresponding spectral bands, to generate a corresponding mask (62), which includes a respective plurality of pixels, each pixel of the mask (62) being relative to a corresponding portion of the component (1), the first neural network (40) being further such that each pixel of the mask (62) represents a corresponding first-level estimate, which is indicative of a probability that the portion of the component (1) to which the pixel refers is damaged; applying a second neural network (70) to a data structure (65) that is a function of the mask (62), to generate a second-level estimate (999), which is indicative of a probability that the component (1) is damaged; and detecting (228) whether the component (1) is healthy or damaged, based on the second-level estimate (999).
A method implemented by means of computer (16) so as to detect anomalies of an unknown component, including determining (314) a plurality of zones (9) of the unknown component and performing at least once the steps of: generating (500, 502, 504) a spectrogram relative to an acoustic signal generated by striking a portion (6) of a zone (9) of the unknown component; between a plurality of binary classifiers (70) each one relative to a corresponding zone (9) of the unknown component, selecting (507) the binary classifier (70) relative to the struck zone, each one of said binary classifiers (70) classifying spectrograms relative to acoustic signals generated by striking the corresponding zone on respective two classes indicative of a spectrogram relative to an acoustic signal generated by striking an undamaged version or a damaged version of the corresponding zone (9) respectively; by means of the selected binary classifier, performing (508) a classification of the spectrogram in one of the respective two classes; and detecting (510) the presence of an anomaly in the struck zone of the unknown component, on the basis of the classification performed by the selected binary classifier.
An aircraft capable of hovering is described, comprising a motor member; a rotor connected to the motor member; a transmission shaft rotatable around a first axis and adapted to drive the rotor; and a transmission interposed between the motor member and the rotor and comprising a planetary gear formed by a sun rotatable around a second axis; a crown that is angularly fixed; and two satellites meshing, each, with the crown and the sun, and rotatable around respective third axes, which are, in turn, rotatable around the second axis; and a satellite carrier rotatable around the second axis and comprising two first pins with respect to which the satellites are rotatable around the respective third axes; the transmission comprises an interface, angularly integral with the satellite carrier around the second axis and said transmission shaft around the first axis; the interface being coupled to said satellite carriers and the transmission shaft so as to allow an angular misalignment between the second axis and a portion of the interface.
The disclosure relates to a system for sensing and recognizing acoustic and/or vibrational anomalies. The system comprises: a unit using optical fiber for the distributed acoustic and/or vibrational sensing of at least one acoustic and/or vibrational anomaly and for generating an alarm signal representative of the sensing of such at least one anomaly; one or more acoustic-electric transducers to sense one or more ambient audio signals associated with the at least one acoustic and/or vibrational anomaly and to convert such ambient audio signals into electrical signals; an audio classifier module configured to classify the electrical signals generated based on at least one algorithm for data analysis and machine learning of information from the data, to generate a classification signal; a correlator module configured to receive the alarm signal and the classification signal and to compare such signals to generate a qualified alarm signal.
A description is provided of a planetary gear comprising a sun rotatable around a first axis, a crown angularly fixed with respect to the first axis; two satellites that are meshing, rotatable around respective second axes; a satellite carrier rotatable around the first axis and comprising at least two first pins with respect to which the satellites are rotatable around respective second axes (I); and a plurality of bearings comprising: a first ring defining a first raceway that is at least partially spherical; a second ring defining a second raceway; and a plurality of rolling bodies shaped as an hourglass rolling on the first spherical raceway and a second raceway; each rolling body being in contact with the raceways at a line with axial ends lying on respective straight lines tilted between them and converging in a point lying on a median plane of the rolling body and on the second axis; the straight lines define a first angle, whose bisector lies on the first median.
F16H 57/08 - General details of gearing of gearings with members having orbital motion
B64D 35/00 - Transmitting power from power plants to propellers or rotorsArrangements of transmissions
F16C 19/38 - Bearings with rolling contact, for exclusively rotary movement with bearing rollers essentially of the same size in one or more circular rows, e.g. needle bearings for both radial and axial load with two or more rows of rollers
Method implemented through a computer for detecting the execution, by an aircraft, of a manoeuvre belonging to a macrocategory among a plurality of macrocategories, including: receiving a data structure with a plurality of time series of values of quantities relating to a flight of the aircraft; for each time duration among a plurality of predetermined time durations, selecting a corresponding subset of the data structure and extracting a corresponding feature vector; on the basis of the feature vectors, generating a corresponding input macrovector and applying to the input macrovector an output classifier to generate estimates indicative of the probability that the aircraft was performing manoeuvres belonging to the macrocategories.
A method is described for manufacturing a structural element in composite material extending along a straight or curvilinear longitudinal direction, having a Z-shaped cross section and comprising, in its final configuration, a central web and two flanges extending at a given final angle from opposite end portions of the web in respective directions opposite to one another; the method including the steps of: arranging a plurality of layers of composite material on a shaped portion of a forming mold; laminating the layers on the shaped portion so that the web is arranged, at least partially, in its final configuration, that a first flange is arranged in its final configuration at the final angle with respect to the portion of the web arranged in its final configuration, and that a second flange is arranged in its initial configuration at an initial angle distinct from, and greater than, said final angle with respect to the portion of the web arranged in its final configuration; moving a movable portion of the forming mold, which is movable with respect to a fixed portion of the forming mold, from a rest position to a bending position; displacing the second flange from the initial configuration into a final configuration in which it is at said final angle with respect to the portion of the web arranged in its final configuration; the step d) of displacing being carried out by means of the step c) of moving.
B64F 5/10 - Manufacturing or assembling aircraft, e.g. jigs therefor
B29C 70/38 - Automated lay-up, e.g. using robots, laying filaments according to predetermined patterns
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
B29C 70/46 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs
B29C 70/54 - Component parts, details or accessoriesAuxiliary operations
72.
METHOD OF MANUFACTURING MONOLITHIC STRUCTURE IN COMPOSITE MATERIAL FOR WINGS OR EMPENNAGES OF AIRCRAFT
The invention relates to a monolithic structure in composite material manufactured starting from a fiber-reinforced prepreg material and comprises two walls facing each other and at least one interconnection element extending transversely between the walls, connected to them and delimiting with the latter respective elongated cavities; wherein the walls extend symmetrically at opposite sides of a direction; the interconnection element is a rib extending transversely to the aforesaid direction; at least one wall has a sandwich configuration and comprises two panels facing each other and at least one spar member, which extends transversely between the panels, is connected to them, delimits with the latter respective elongated cavities and extends transversally to the rib.
B64F 5/10 - Manufacturing or assembling aircraft, e.g. jigs therefor
B29C 70/00 - Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
B29C 70/30 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or coreShaping by spray-up, i.e. spraying of fibres on a mould, former or core
B29C 70/68 - Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts by incorporating or moulding on preformed parts, e.g. inserts or layers
The artefact comprises a flat or curved body substantially made of metal or metal alloy or composite material and comprising one or more ice protection panel(s). The ice protection panel(s) comprise a heater film and at least one ply made of CFRC and/or GFRC. The heater film includes a thermoplastic polymeric matrix containing polar groups, and at least one graphene or graphitic layer which is electrically conductive, or a thermosetting resin, and functionalized with elastomeric nanodomains containing dispersed electrical conductive carbon–based nanoparticles. The heater film is also provided of electrodes and is placed between said at least one ply made of CFRC and/or GFRC and an outer protective coating, or is placed between two plies independently made of CFRC and/or GFRC.
H05B 3/14 - Heating elements characterised by the composition or nature of the materials or by the arrangement of the conductor characterised by the composition or nature of the conductive material the material being non-metallic
B64D 15/12 - De-icing or preventing icing on exterior surfaces of aircraft by electric heating
H05B 3/34 - Heating elements having extended surface area substantially in a two-dimensional plane, e.g. plate-heater flexible, e.g. heating nets or webs
74.
INDICATOR FOR AN AIRCRAFT CAPABLE OF HOVERING AND METHOD FOR ASSISTING PERFORMING A MANOEUVRE FOR THE AFORESAID AIRCRAFT
It is disclosed an indicator for an aircraft capable of hovering, comprising a first indication associated to the value of vertical speed of the aircraft itself; the indicator comprises a first area wherein a second indication can be displayed that is associated to a Vortex Ring State condition being reached.
Aircraft (1) capable of hovering comprising a fuselage (2), at least one rotor (3a, 3b, 4) that is rotatable with respect to the fuselage (2), electrical drive means adapted to rotate the rotor (3a, 3b, 4) and electrically powered by a battery (9), and a cooling system (10) of the battery (9). Said cooling system (10) comprises, in turn, a first opening (20) for the air to enter, second openings (21) for the air to escape and a passage (22), which places the first opening (20) in fluidic communication with the second openings (21) and within which the battery (9) is placed. The cooling system (10) further comprises a fan (23) adapted to increase the kinetic energy of the air contained in the passage (22) and which is operated when the forward speed (v) of the aircraft (1) with respect to the ground is lower than a speed threshold value (v0) and/or when the temperature (T) of the battery (9) exceeds a temperature threshold value (T0).
B64D 33/08 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
B64D 27/24 - Aircraft characterised by the type or position of power plants using steam or spring force
B64D 13/00 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space
B64C 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
B64C 27/28 - Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with forward-propulsion propellers pivotable to act as lifting rotors
B64D 13/06 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned
76.
INNOVATIVE THREE-DIMENSIONAL U-SHAPED ARCHITECTURE FOR TRANSMIT/RECEIVE MODULES OF AESA SYSTEMS
The invention concerns an active electronically steerable antenna including: a planar or quasi-planar radiating array configured to transmit and/or receive radiofrequency or microwave signals, and a plurality of three-dimensional U-shaped modules, each arranged behind, and coupled to, a respective planar or quasi-planar radiating subarray of N radiating elements arranged in two rows or columns, each of N/2 radiating elements, N being an even integer. Each three-dimensional U-shaped module comprises: a respective base wall; two respective side walls that are orthogonally arranged with respect to the respective base wall so as to form therewith a respective three-dimensional U-shaped structure, and are arranged, each, behind a respective row or column of N/2 radiating elements of the respective planar or quasi-planar radiating subarray; and respective transmit and/or receive electronics distributed on said respective base and side walls and configured to implement N respective transmit and/or receive modules. For each three-dimensional U-shaped module, the respective transmit and/or receive electronics includes: for each respective side wall, N/2 respective transmission and/or reception front-end modules that are mounted on said respective side wall, are coupled to the N/2 radiating elements of the respective row or column of the respective planar or quasi-planar radiating subarray, and are configured to implement power amplifiers, low noise amplifiers, and switches or circulators; and respective base wall electronics mounted on the respective base wall, connected to the N respective transmission and/or reception front-end modules and configured to carry out beam steering functions including signal phase-shifting, and attenuation and/or amplification functions.
H01Q 21/20 - Arrays of individually energised antenna units similarly polarised and spaced apart the units being spaced along, or adjacent to, a curvilinear path
H04B 7/06 - Diversity systemsMulti-antenna systems, i.e. transmission or reception using multiple antennas using two or more spaced independent antennas at the transmitting station
77.
ASSEMBLY FOR MOUNTING AN UNDERWING PYLON TO A RIB OF AN AIRCRAFT WING
An assembly for removably mounting an underwing pylon to a rib of an aircraft wing is provided. The assembly has a prismatic body insertable into a prismatic cavity of the underwing pylon, a threaded retaining element having an upwardly tapered outer conical surface, and a vertical threaded pin inserted through a vertical through hole of the prismatic body. The assembly has an anti-rotation device for rotationally locking the threaded retaining element to the prismatic body relative to a vertical axis.
A method for the integration of continuous J shaped spars in extended panels of composite material in which J shaped spars are each arranged on a rectilinear support having at least one right triangle shaped portion, and the spars carried by the respective rectilinear supports are subsequently arranged on a stratified structure carried by a mould. A vacuum bag is created which covers the stratified structure, the rectilinear supports, and the J shaped spars. Holes are created in the vacuum bag at respective connection points made along each rectilinear support. A supporting structure provided with hooking and adjusting elements with the connection points adjusts the position of each hooking and adjusting element with respect to the supporting structure in order to position the rectilinear support in a direction parallel to the vertical so that the position of the end portion of the J shaped spar, with respect to the mould, corresponds to that foreseen by the design.
B29C 65/00 - Joining of preformed partsApparatus therefor
B29C 65/02 - Joining of preformed partsApparatus therefor by heating, with or without pressure
B29C 65/48 - Joining of preformed partsApparatus therefor using adhesives
B29C 65/78 - Means for handling the parts to be joined, e.g. for making containers or hollow articles
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
B29C 70/54 - Component parts, details or accessoriesAuxiliary operations
A passive multi-frequency damping device for damping vibrations of an aircraft has a support structure, a plurality of N metal damping masses, each having a respective n-th mass, N being a natural number greater than or equal to 2, and n being a natural number from 1 to N, a plurality of N elastic elements each having a respective n-th stiffness, and each being glued to both the support structure and a respective n-th damping mass to support the respective n-th damping mass on the support structure so that the respective n-th damping mass is free to vibrate relative to the support structure. For each n from 2 to N, each n-th damping mass is arranged to at least partially surround an n−1-th damping mass. The first damping mass has a solid semi-cylindrical shape, and the remaining damping masses have a hollow semi-cylindrical shape.
A microphone calibration method, in particular a microphone for aeronautical use, comprising the following steps, coupling a reference microphone to a first end of a first standing-wave tube; coupling a microphone subjected to calibration to a first end CI a) of a second standing-wave tube; supplying an acoustic input signal to the second end of the first and second tubes so that plane standing-waves propagate in the tubes; measuring the sound pressure of the acoustic signal detected by the first and second microphones; increasing the sound pressure of the acoustic input signal from an initial value until a first sound pressure value DB1r is measured by means of the reference microphone and simultaneously detecting a first sound pressure value DB1t by means of the microphone subjected to calibration; further increasing the sound pressure of the acoustic input signal by a first amount ΔDB1 and detecting a second sound pressure value DB2r by means of the reference microphone and simultaneously detecting a second sound pressure value DB2t by means of the microphone subjected to calibration; decreasing the sound pressure of the acoustic input signal by a second amount −ΔDB2 greater than the first amount ΔDB1 and detecting a third sound pressure value DB3r by means of the reference microphone and simultaneously detecting a third sound pressure value DB3t by means of the microphone subjected to calibration; again, increasing the sound pressure of the acoustic input signal by a third amount ΔDB3 and detecting a fourth sound pressure value by means of the reference microphone and simultaneously detecting a fourth sound pressure value with the microphone subjected to calibration; the sum of the first and third amounts corresponding to the absolute value of the second amount; controlling whether the fourth sound pressure value detected by means of the microphone subjected to calibration substantially corresponds to the first sound pressure value DB1t by means of the same microphone subjected to calibration and in the case of a positive outcome detecting a correct calibration of the microphone.
The turret, in particular for naval applications, comprises a traversing part and an elevating part integrally rotatable with the traversing part. There is a barrel supported by the elevating part and integrally rotatable therewith about the elevation axis (X1). The barrel is configured to fire guided ammunition through itself. An ammunition guidance system (24) is configured to direct a guided piece of ammunition towards a target by means of an electromagnetic emission. A moving device (100), whereon the ammunition guidance system (24) is mounted, is configured to move the latter in such a way as to orient the electromagnetic emission towards the target. The moving device (100) is mounted to the traversing part (14) and comprises a frame (102) that rotatably supports the ammunition guidance system (24) about an azimuthal or traversing movement axis (Y1) and a zenithal or elevation movement axis (X1).
Fire fighting drone comprising an exoskeleton (2) defining an internal space (3) extending along an axis H and a flexible bag (4) stably housed in the internal space (3), provided with a release valve (6) and configured to contain a fire fighting liquid (7); a support structure (8) provided with a plurality of thrusters (11) adapted to perform a thrust that enables the support structure (8) to be supported in flight; the support structure (8) is connected to a first end portion (2-a) of the exoskeleton (2); a plurality of movable directional wings (10) carried by the exoskeleton (2), extending outwards from the exoskeleton itself and angularly movable relative to the exoskeleton (2) around respective axes H transverse to the axis H; an electronic control unit adapted to control the thruster (11), to generate the release signal and adapted to control the actuators that perform the rotation of the wings; the electronic control unit is configured to control said wings to allow the rotation of the wings during the free-fall phase of said drone which is released from an aircraft and thereby performs a certain trajectory of said drone from the aircraft to a launch zone; the electronic unit is configured to enable the discharge of said liquid from said bag and the activation of the thrusters (11) following the discharge of the liquid to enable the flight of the support structure and of the exoskeleton containing the empty bag to a landing zone.
The turret (10), in particular for naval applications, comprises a traversing part (14) and an elevating part (16) integrally rotatable with the traversing part (14). There is a barrel (18) supported by the elevating part (16) and integrally rotatable therewith about the elevation axis (X). The barrel (18) is configured to fire guided ammunition through itself. An ammunition guidance system (24) is configured to direct a guided piece of ammunition towards a target by means of an electromagnetic emission. A protection device (26) is provided, which is configured to assume a closing condition, wherein it encloses and protects the ammunition guidance system (24), and an opening condition, wherein it clears and exposes the ammunition guidance system (24). The ammunition guidance system (24) and the protection device (26) are mounted to the traversing part (14). The traversing part (14) internally defines a reclosable cavity (28) that houses the ammunition guidance system (24), faces forwards, and is configured to be closed by the protection device (26) when the latter is in the closing condition.
A method for manufacturing a panel for an aircraft is provided. The method includes arranging, on a curing surface, a skin of pre-preg composite material, arranging a plurality of pre-formed, uncured composite stringers, each having an open cross section with a web and a base transverse to each other so that a first base portion protrudes toward a first side and a second base portion protrudes toward a second side, arranging the stringers on the skin with the base in contact with the skin, arranging, on each stringer, a respective first mandrel to completely cover the first base portion and a respective second mandrel to completely cover the second base portion, and having the skin and the stringers undergo a co-curing process in autoclave with vacuum bag.
B29C 70/54 - Component parts, details or accessoriesAuxiliary operations
B29C 70/76 - Moulding on edges or extremities of the preformed part
B29C 70/38 - Automated lay-up, e.g. using robots, laying filaments according to predetermined patterns
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
09 - Scientific and electric apparatus and instruments
Goods & Services
Weapons, namely, ballistic weapons; missile counter-measures devices (MCD), namely, military devices designed to prevent sensor-based weapons from acquiring or destroying a target, to be used against torpedoes, missiles or other exploding objects in the nature of ballistic missiles and torpedoes Electronic apparatus used for jamming and decoy counter-measures, namely, electronic transmitters for jamming signals; recorded software for detecting and jamming electronically transmitted signals used for jamming and decoy counter-measures
An aircraft (1) comprising a fuselage (2, 2', 2'') with a nose (4) and a tail (5) arranged on opposite parts to each other along a first longitudinal axis (Y) is described; a pair of half-wings (3) arranged on respective mutually opposite sides of the fuselage (2, 2', 2'); a first and a second rotor (22a, 22b) carried by respective half-wings (3), respectively rotatable around a second and third axis (F, G) inclinable with respect to said fuselage (2, 2', 2''), and independently operable from each other; the aircraft (1) is switchable between a first hovering flight or take-off/landing configuration wherein the fourth and fifth axis (F, G) are arranged orthogonal to said first axis (Y); and a second forward flight configuration wherein the fourth and fifth axis (F, G) are arranged parallel or inclined with respect to said first axis (Y); the aircraft (1) further comprising a tail portion (6) comprising a first aerodynamic surface (8), and a third and a fourth rotor (21a, 21b) rotatable around a fixed fourth and a fifth axis (D, E); and support means (31a, 31b) of the third and fourth rotor (21a, 21b) connected to a corresponding said half-wing (3) and to a corresponding said fin (52).
A fuselage (2, 2', 2'') for a convertible aircraft (1) is described, comprising a nose (4) and a tail (5) arranged on mutually opposite sides along a first longitudinal axis (Y) of the fuselage (2); a first portion (100) and a second portion (101) arranged one after the other, proceeding along the first axis (Y) from the nose (4) towards the tail (5); and an electric power source (102) connectable with at least one electric powertrain (40a, 40b, 40c, 40d, 40e, 40f) and arranged inside the second portion (101); the first and second portion (100, 101) define respectively a first and a second section (110, 111, 111'') in a plane orthogonal to the first axis (Y); the second section (111) defines at least one air intake (120) that is open towards the outside of the fuselage (2) itself and fluidically connected with the source (102) so as to convey, in use, a flow of cooling air onto the source (102) itself following the forward motion of the aircraft (1); the second section (111, 111'') having a larger area than the first section (110); the air intake (120) being arranged at a sidewall (19) of the second portion (101) and externally to the first portion (100) and in a view parallel to the first axis (Y).
B64D 27/24 - Aircraft characterised by the type or position of power plants using steam or spring force
B64D 33/08 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
B64C 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
B64C 7/00 - Structures or fairings not otherwise provided for
B64C 1/14 - WindowsDoorsHatch covers or access panelsSurrounding frame structuresCanopiesWindscreens
B64C 1/00 - FuselagesConstructional features common to fuselages, wings, stabilising surfaces or the like
B64U 101/61 - UAVs specially adapted for particular uses or applications for transporting passengersUAVs specially adapted for particular uses or applications for transporting goods other than weapons for transporting passengers
88.
METHOD FOR IDENTIFYING MALFUNCTION CONDITIONS OF SENSORS THAT MEASURE THE AMOUNT OF FUEL IN THE TANKS OF AN AIRCRAFT
Method for identifying malfunction conditions of the sensors that measure the amount of fuel in the tanks of an aircraft (1) provided with at least one first tank (2/6) arranged on a first side of the aircraft and at least one second tank (4/8) arranged on a second side, each first and second tank (2/6; 4/8) is provided with a plurality m of sensors (11) detecting the level of fuel within the respective tank (2/6 and 4/8). The method performs a symmetry control wherein the level gradients (11) associated with the first tank (2/6) and the second tank (4/8) are compared to each other; and if the values of the compared gradients are close, a consistency condition is detected. As an alternative to the symmetry control, a discontinuity control is carried out wherein the step of comparing the consumption gradient associated with each sensor (11) with a reference gradient comprising an average consumption gradient of the other sensors and/or with the total consumption gradient is carried out.
G01F 25/20 - Testing or calibration of apparatus for measuring volume, volume flow or liquid level or for metering by volume of apparatus for measuring liquid level
B64D 37/00 - Arrangements in connection with fuel supply for power plant
89.
METHOD OF REALIZATION OF AN ITEM FOR AERONAUTICAL APPLICATION WITH HYBRID COMPOSITE MATERIALS BY MEANS OF ADDITIVE TECHNOLOGY
A method of realization of an aeronautical item with hybrid composite materials by means of additive technology comprising the steps of: design of the product by means of a three-dimensional mathematical model which defines, in a reference system, the shape and dimensions and includes the information associated with the areas of the item that must be reinforced according to the level of stress; deposition, by means of additive technology, of a matrix in polymeric material and of reinforcing fibers according to the mathematical model; deposition of one or more continuous fibers made of different materials along articulated paths in correspondence with the areas that must be reinforced according to the level of stress (continuous fibers oriented along paths defined by the directions of the loads or in any case in the directions provided in the design phase).
B29C 64/118 - Processes of additive manufacturing using only liquids or viscous materials, e.g. depositing a continuous bead of viscous material using filamentary material being melted, e.g. fused deposition modelling [FDM]
A roller unit for moving a slat of an aircraft wing is provided. The roller unit is adjustable in height and axial position to adjust a gap between an idle roller and a guide rail integral with the slat. The idle roller is carried by an eccentric pin having a stem portion with a threaded portion and an axially grooved end portion. A threaded annular element cooperates with the threaded portion of the stem portion to define a desired axial position of the idle roller. An anti-rotation annular element, coupled in an axially slidable manner with the grooved end portion of the stem portion, may be coupled with the threaded annular element to prevent rotation thereof on the threaded portion of the stem portion. The threaded annular element and the anti-rotation annular element are tightened together between a pair of nuts.
The invention relates to equipment (10) for making a structural element (1) of composite material having a longitudinal axis (A) and an axial cavity (2). The equipment (10) comprises a support frame (11) and a laminating mandrel (12), which is mounted on the support frame (11) so that it can rotate about its own central axis (B) and defines an outer laminating surface (13); the support frame (11) comprises two vertical headers (14, 15), facing each other and parallel to each other, and longitudinal connecting means (16) for longitudinally connecting the headers (14, 15); each header (14, 15) comprises a fixed portion (17) and a movable portion (18), coaxially receiving the laminating mandrel (12) and rotatable about the central axis (B) in relation to the fixed portion (17); the laminating mandrel (12) comprises a central shaft (26, 26' ), a plurality of sectors (30) angularly spaced apart about the central axis (B), and a plurality of linear actuators (31) extending between the central shaft (26, 26' ) and respective sectors (30) to move the sectors (30) themselves between an expanded laminating position and a contracted position; the equipment (10) further comprises first constraining means (35) for connecting in a releasable manner the sectors (30), arranged in the expanded laminating position, to the movable portions (18) of the headers (14, 15), and second constraining means (36) connecting the linear actuators (31) to the sectors (30) in a releasable manner so as to enable the extraction of the central shaft (26, 26' ) and linear actuators (31) from the equipment (10) in the condition in which the sectors (30), in the expanded position, are connected to the movable portions (18) of the headers (14, 15) by means of the first constraining means (35).
B29C 33/48 - Moulds or coresDetails thereof or accessories therefor with means for, or specially constructed to facilitate, the removal of articles, e.g. of undercut articles with means for collapsing or disassembling
B29C 70/32 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or coreShaping by spray-up, i.e. spraying of fibres on a mould, former or core on a rotating mould, former or core
B29C 70/54 - Component parts, details or accessoriesAuxiliary operations
92.
EQUIPMENT AND PROCESS FOR MAKING A STRUCTURAL ELEMENT IN COMPOSITE MATERIAL
The invention relates to equipment (10) for making a structural element (1) of composite material having a longitudinal axis (A) and an axial cavity (2). The equipment (10) comprises a support frame (11) and a laminating mandrel (12), which is mounted on the support frame (11) so that it can rotate about its own central axis (B) and defines an outer laminating surface (13); the support frame (11) comprises two vertical headers (14, 15), facing each other and parallel to each other, and longitudinal connecting means (16) for longitudinally connecting the headers (14, 15); each header (14, 15) comprises a fixed portion (17) and a movable portion (18), coaxially receiving the laminating mandrel (12) and rotatable about the central axis (B) in relation to the fixed portion (17); the laminating mandrel (12) comprises a central shaft (26, 26' ), a plurality of sectors (30) angularly spaced apart about the central axis (B), and a plurality of linear actuators (31) extending between the central shaft (26, 26' ) and respective sectors (30) to move the sectors (30) themselves between an expanded laminating position and a contracted position; the equipment (10) further comprises first constraining means (35) for connecting in a releasable manner the sectors (30), arranged in the expanded laminating position, to the movable portions (18) of the headers (14, 15), and second constraining means (36) connecting the linear actuators (31) to the sectors (30) in a releasable manner so as to enable the extraction of the central shaft (26, 26' ) and linear actuators (31) from the equipment (10) in the condition in which the sectors (30), in the expanded position, are connected to the movable portions (18) of the headers (14, 15) by means of the first constraining means (35).
B29C 70/32 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or coreShaping by spray-up, i.e. spraying of fibres on a mould, former or core on a rotating mould, former or core
B29C 33/48 - Moulds or coresDetails thereof or accessories therefor with means for, or specially constructed to facilitate, the removal of articles, e.g. of undercut articles with means for collapsing or disassembling
B29D 99/00 - Subject matter not provided for in other groups of this subclass
B64C 1/00 - FuselagesConstructional features common to fuselages, wings, stabilising surfaces or the like
B29C 70/54 - Component parts, details or accessoriesAuxiliary operations
93.
COHERENT BEAM COMBINATION SYSTEM AND CONTROL METHOD THEREOF
The coherent beam recombination (CBC) system (1) provides an output recombined beam (2) and comprises: a laser source (3) providing a source beam (8) with linewidth; a beam broadener (5) providing a broadened beam (10) from the source beam; a splitter (7) splitting the broadened beam into a plurality of secondary beams (12A-12D); a plurality of channels (20A-20D) coupled to the splitter. Each channel receives a respective secondary beam (12A-I2D) and provides a respective intermediate beam (21A-21D). Each channel has an optical amplifier (40), a phase modulator (42), an optical delay line (44), and an opto-mechanical element (47). The CBC system further comprises an optical sensor (23, 24) that provides a detection signal (TNT, IMG) indicative of an intensity of a received optical beam; a focusing optics (17) that receives the intermediate beams (21A- 21D), provides the output recombined beam (2) from a first portion of each intermediate beam, and provides a sampled recombined beam (63) to the optical sensor from a second portion (63) of each intermediate beam. The CBC system further comprises a control unit (30) coupled to the optical sensor and the plurality of channels. The control unit comprises a phase-locking module (26) configured to: provide a plurality of phase control signals (m, U2, U3, U4) to the phase modulators (42); receive the detection signal (INT) from the optical sensor, indicative of an intensity of the sampled recombined beam; calculate a cost function (J) from the detection signal (INT), wherein the cost function is a function of the intensity of the sampled recombined beam; perform an optimization algorithm of the cost function, configured to maximise the intensity of the sample recombined beam; and provide a plurality of updated phase control signals, based on a result of the optimization algorithm.
H01S 3/10 - Controlling the intensity, frequency, phase, polarisation or direction of the emitted radiation, e.g. switching, gating, modulating or demodulating
94.
METHOD FOR CONTROLLING AN AIRCRAFT CAPABLE OF HOVERING AND RELATIVE AIRCRAFT
A method for controlling an aircraft capable of hovering is described, comprising a first engine; a second engine; at least one rotor; and a transmission interposed between the first and second engine and the rotor; the transmission comprises a first and a second inlet connected respectively to a first outlet member of the first engine and to a second outlet member of the second engine; the method comprises step i) of placing the in a first configuration, in which the first and second engine make available a first and a second power value; or in a second configuration, in which the first engine (makes available a third power value greater than the first power value to the first inlet, and the second engine delivers a nil power value to the second inlet; the method also comprises, characterised in that it comprises the steps of ii) detecting a series of parameters associated with the operating conditions of the aircraft; and iii) enabling the transition of the aircraft from the first configuration to the second configuration, when the parameters assume respective first values.
B64D 31/10 - Initiating means actuated automatically in response to power plant failure for preventing asymmetric thrust
B64D 35/08 - Transmitting power from power plants to propellers or rotorsArrangements of transmissions characterised by the transmission being driven by a plurality of power plants
G05D 1/00 - Control of position, course, altitude or attitude of land, water, air or space vehicles, e.g. using automatic pilots
95.
COHERENT BEAM COMBINATION SYSTEM AND CONTROL METHOD THEREOF
12344) to the phase modulators (42); receive the detection signal (INT) from the optical sensor, indicative of an intensity of the sampled recombined beam; calculate a cost function (J) from the detection signal (INT), wherein the cost function is a function of the intensity of the sampled recombined beam; perform an optimization algorithm of the cost function, configured to maximise the intensity of the sample recombined beam; and provide a plurality of updated phase control signals, based on a result of the optimization algorithm.
H01S 3/10 - Controlling the intensity, frequency, phase, polarisation or direction of the emitted radiation, e.g. switching, gating, modulating or demodulating
H01S 3/13 - Stabilisation of laser output parameters, e.g. frequency or amplitude
H01S 3/23 - Arrangement of two or more lasers not provided for in groups , e.g. tandem arrangement of separate active media
G02B 6/42 - Coupling light guides with opto-electronic elements
G02B 27/09 - Beam shaping, e.g. changing the cross-sectioned area, not otherwise provided for
Transmission assembly (3, 3', 3'', 3''' 3'''') for an aircraft (1) capable of hovering, comprising : a first and a second member (7, 8) and support means (9) of the first member (7) with respect to the second member (8); a primary lubrication circuit (20) comprising a primary tank (11) of a lubricating fluid and primary fluidic supply means (12) for supplying fluid to the support means (9); and an emergency lubrication circuit (22) comprising an emergency tank (23) of lubricating fluid fluidically connected to the primary tank (11); and auxiliary fluidic supply means (30) of the lubricating fluid to the support means (9), comprising a nozzle (24); the auxiliary fluidic supply means (30) comprise a dosing device (31, 31', 31'', 31''' 31'''') and a fluidic line (32), which fluidically connects the emergency tank (23) with the dosing device (31, 31', 31'', 31''' 31''''); the dosing device (31, 31', 31", 31''' 31'''') comprising a passage (33, 33'''') for the lubricating fluid from the fluidic line (32) to the nozzle (24), which comprises a plurality of concentrated pressure drop sections (6, 6''''), which are distinct and spaced apart from each other.
A helicopter is described comprising a motor member comprising an output shaft and a first stator rotatably supporting the output shaft around a first axis; a main rotor adapted to provide the lift necessary for the support and the thrust necessary for the movement of the helicopter; a transmission interposed between the motor member and the main rotor; the transmission rotatable around a second axis and a second stator rotatably supporting the input shaft around the second axis; the helicopter also comprises a joint interposed between the first and second stator, angularly fixed with respect to the first axis, and configured to allow an inclination between the first and second stator in a plane parallel to said first axis; the joint comprises a first corrugated element made of an elastically deformable material, interposed between said first and second stator, and adapted to allow the inclination through elastic deformation.
A process for manufacturing a structural component made of composite material comprising a skin and at least one stiffening stringer applied rigidly and integrally to one face of the skin. The process comprises a) arranging, on a tool, a plurality of first layers of uncured or pre-cured composite material, forming the stringer and having a raised portion protruding from at least one flange; b) arranging, on said tool, a plurality of second layers of uncured or pre-cured composite material forming said skin; c) making a face of said skin and flange adhere to each other; d) applying predetermined temperature and pressure on the assembly, possibly curing the uncured material and rigidly joining said skin to said stringer; e) performing a cutting operation on the free end side edge/s of said flange; and f) cover said end side edge/s of the end of said flange with a coating of composite material.
B29C 70/30 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or coreShaping by spray-up, i.e. spraying of fibres on a mould, former or core
B29C 70/54 - Component parts, details or accessoriesAuxiliary operations
B29C 70/88 - Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts characterised primarily by possessing specific properties, e.g. electrically conductive or locally reinforced
99.
PROCESS FOR MANUFACTURING A STRUCTURAL COMPONENT IN COMPOSITE MATERIAL STIFFENED WITH AT LEAST ONE STRINGER
A process for manufacturing a structural component made of composite material comprising a skin and at least one stiffening stringer applied rigidly and integrally to one face of the skin. The process comprises a) arranging, on a tool, a plurality of first layers of uncured or pre-cured composite material, forming the stringer and having a raised portion protruding from at least one flange; b) arranging, on the tool, a plurality of second layers of uncured or pre-cured composite material forming the skin; c) making a face of the skin and the flange of the stringer adhere to each other; d) applying a predetermined temperature and pressure on the assembly to compact the layers together, possibly curing the uncured material and rigidly joining the skin to the stringer; and e) performing a cutting operation on the free end side edge/s of the flange in a slanted direction.
B29C 70/30 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or coreShaping by spray-up, i.e. spraying of fibres on a mould, former or core
B29C 70/54 - Component parts, details or accessoriesAuxiliary operations
B29C 70/88 - Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts characterised primarily by possessing specific properties, e.g. electrically conductive or locally reinforced
B64F 5/10 - Manufacturing or assembling aircraft, e.g. jigs therefor
An isostatic mounting system is described to support a sensor and to minimise the thermal conductivity between the sensor and a carrier thereof. An isostatic mounting system comprises at least one support foot configured to be fixed, in use, to a structure of the carrier, and at least one leg extending from the support foot. The support foot is made of a full solid material and the leg has a lattice structure made of the same material of the support foot.
F16M 11/22 - Undercarriages with or without wheels with approximately constant height, e.g. with constant length of column or of legs
B22F 5/10 - Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product of articles with cavities or holes, not otherwise provided for in the preceding subgroups
F16M 13/02 - Other supports for positioning apparatus or articlesMeans for steadying hand-held apparatus or articles for supporting on, or attaching to, an object, e.g. tree, gate, window-frame, cycle
