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 accessories; Auxiliary operations
3.
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 core; Shaping 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
4.
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.
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 systems; Multi-antenna systems, i.e. transmission or reception using multiple antennas using two or more spaced independent antennas at the transmitting station
6.
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 parts; Apparatus therefor
B29C 65/02 - Joining of preformed parts; Apparatus therefor by heating, with or without pressure
B29C 65/48 - Joining of preformed parts; Apparatus 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 accessories; Auxiliary operations
8.
MICROPHONE CALIBRATION METHOD, IN PARTICULAR MICROPHONE FOR AERONAUTICAL USE
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.
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 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 accessories; Auxiliary 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
11.
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.
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 for preventing asymmetric thrust upon failure of one power plant
B64D 35/08 - Transmitting power from power plant to propellers or rotors; Arrangements 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. automatic pilot
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 comprises, in turn, an input shaft 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 core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
B29C 70/54 - Component parts, details or accessories; Auxiliary 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
16.
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 core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
B29C 70/54 - Component parts, details or accessories; Auxiliary 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 articles; Means for steadying hand-held apparatus or articles for supporting on, or attaching to, an object, e.g. tree, gate, window-frame, cycle
A rotor for an aircraft is described, comprising an input shaft rotatable around a first axis; an output member rotatable around a second axis; a coupling element functionally interposed between the input shaft and the output member and adapted to transmit the motion from the input shaft to the output member; the coupling element is configured to allow, in use, a fixed or variable inclination between the respective first and second axes; the coupling element comprises at least a first corrugated element made of an elastically deformable material; the first corrugated element allows the inclination through elastic deformation.
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
B64C 27/82 - Rotorcraft; Rotors 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
F16D 3/72 - Yielding couplings, i.e. with means permitting movement between the connected parts during the drive with the coupling parts connected by one or more intermediate members with axially-spaced attachments to the coupling parts
19.
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.
A helicopter is described comprising a fuselage elongated along a first axis and extending between a nose and a tail boom; a tailplane with a pair of first aerodynamic surfaces elongated along a second axis; the first and second axis define a first plane; the helicopter comprises a pair of elements transversal to the first aerodynamic surfaces; and a pair of second aerodynamic surfaces generating respective second aerodynamic forces, connected to first elements, and facing and spaced from respective first aerodynamic surfaces; each second aerodynamic surface comprises one first root end connected to the respective said element, a second free end spaced from said tail boom, a first leading edge, a first trailing edge opposite to said first leading edge, a first chord at said first root end and a second chord at said second free end parallel to said first axis; the first and the second chord define a second plane tilted with respect to said first plane.
B64C 27/82 - Rotorcraft; Rotors 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
A product comprising a substrate and a multilayer coating for the thermal control of a surface comprising a first inner layer intended to be deposited on said surface, a second intermediate layer applied on said first inner layer and a third outer layer applied on said second intermediate layer in which: said first inner layer comprises a co-dispersion of conductive nanoparticles and dielectric nanoparticles
An aircraft with a motor bay is described; a motor system with a discharge duct; a heat exchanger arranged outside said motor system; a first air intake; a first duct along which the heat exchanger is arranged; a first converging nozzle having a downstream section fluidically connected with the discharge duct and with the first duct so as to create a first flow rate of air adapted to cool the heat exchanger; and a second air intake that is open in the motor bay and distinct from the first air intake; a second converging nozzle having a second downstream section fluidically connected with the discharge duct and with the motor bay, so as to create a second flow rate of cooling air of the motor bay directed from the second air intake towards the discharge duct and by-passing the motor system.
A thrust reverser system for a turbofan propulsion system of an aircraft includes a fixed structure and a translating structure configured to internally define a sequential flow path for air. The translating structure is slidable along an axial direction between a stowed position in which the translating structure is connected to the fixed structure, and an opening position in which the translating structure is spaced apart from the fixed structure in the axial direction to define a circumferential opening for outflow of air to external environment. An iris mechanism has a plurality of blades jointly movable between a rest configuration in which the blades jointly define a passage for air, and a deployed configuration in which the blades at least partially occlude a bypass duct of the turbofan propulsion system.
F02K 1/72 - Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow
F02C 7/20 - Mounting or supporting of plant; Accommodating heat expansion or creep
F02K 1/60 - Reversing jet main flow by blocking the rearward discharge by means of pivoted eyelids or clamshells, e.g. target-type reversers
F02K 1/68 - Reversers mounted on the engine housing downstream of the fan exhaust section
A cargo door for an aircraft having a plurality of locking devices spaced near an edge of the cargo door, at least one vent panel, a control handle, and a torsion shaft actuating a plurality of pins to lock and unlock the plurality of locking devices is provided. A first drive connects the control handle to the torsion shaft to rotate the torsion shaft following a locking or unlocking command imparted to the control handle. A second drive connects the torsion shaft to the at least one vent panel to open or close the at least one vent panel following a rotation of the torsion shaft. The torsion shaft is a double shaft having two coaxial and rotationally integral shafts, namely an inner control shaft and an outer tubular control shaft.
E05C 9/00 - Arrangement of simultaneously-actuated bolts or other securing devices at well-separated positions on the same wing
E05C 9/08 - Arrangement of simultaneously-actuated bolts or other securing devices at well-separated positions on the same wing with a rotary bar for actuating the fastening means
A rotor for an aircraft is described having: a support angularly fixed with respect to an axis and housing a power source; a unit rotatable about axis and housing an electrical load of the resistive type; and a power supply system for the electrical load and comprising: a first transformer electrically interposed between the power source and the load; the first transformer comprises: a first winding arranged on the support and a second winding arranged on the unit, a stator carried by the support, rotationally fixed with respect to axis and to which the first winding is fixed; and a rotor operatively connected to the unit and to which the second winding is fixed; the power supply system comprises a capacitive circuit electrically connected to the first transformer, so as to reduce the reactive power absorbed by the rotary transformer.
B64D 15/12 - De-icing or preventing icing on exterior surfaces of aircraft by electric heating
B64D 45/00 - Aircraft indicators or protectors not otherwise provided for
F16C 19/06 - Bearings with rolling contact, for exclusively rotary movement with bearing balls essentially of the same size in one or more circular rows for radial load mainly with a single row of balls
H01F 21/04 - Variable inductances or transformers of the signal type continuously variable, e.g. variometers by relative movement of turns or parts of windings
26.
METHOD AND DEVICE FOR MONITORING THE OPERATION OF A PAIR OF TURBOPROP ENGINES THROUGH THE NUMERICAL PROCESSING OF AN ACOUSTIC MAGNITUDE
Method for monitoring the operation of a pair of turboprop engines of an aircraft comprising the steps of: detecting the sound pressure generated by the first or second turboprop engine generating a respective first or second signal x(t); iteratively calculating by means of a function Rx/Ry the similarity between the first/second signal x(t)/y(t) at a time T1 and at a time T2 subsequent to time T1; and storing the degrees of similarity calculated in successive iterations in order to detect situations of normal operation of the engines when the degrees of similarity fall in successive iterations within the interval of a first value and to detect a potential fault situation in the engines when the degrees of similarity depart from this interval.
A multifunctional composite material is provided which has a polymeric matrix filled with electrically conductive nanoparticles combined with a self-healing molecular filler selected from the group consisting of molecules and oligomers containing groups acting as donors and acceptors of hydrogen bonds.
H01B 1/24 - Conductive material dispersed in non-conductive organic material the conductive material comprising carbon-silicon compounds, carbon, or silicon
C08L 63/00 - Compositions of epoxy resins; Compositions of derivatives of epoxy resins
28.
HOVER-CAPABLE AIRCRAFT AND LUBRICATION METHOD FOR A MODULE OF A TRANSMISSION UNIT OF SAID AIRCRAFT
An aircraft is described comprising a transmission unit with a first module and a lubrication system; the first module comprises a casing and a movable member; the lubrication system comprises a header, a nozzle fed with the lubricating fluid and designed to feed the lubricating fluid inside the casing of the first module, a collection tank for the lubricating fluid injected by the nozzle, and recirculation means designed to cause the recirculation of the lubricating fluid from the collection tank to the feed header; the first module comprises a valve available in a first configuration, in which it enables the outflow of said lubricating fluid from said module to the recirculation means when the pressure of the lubricating fluid inside the header is greater than a threshold value; and in a second configuration, in which it fluidically isolates the module from the recirculation means when the pressure of the lubricating fluid inside the header is less than the threshold value.
A convertiplane is described that comprises: a fuselage, having a first longitudinal axis and, in turn, comprising a nose and a tail portion; a pair of wings arranged on respective opposite sides of the fuselage, carrying respective rotors and generating a lift value; and a pair of engines operatively connected to respective rotors; each rotor comprising a mast rotatable about a second axis between a helicopter configuration and an aeroplane configuration; each rotor is interposed between the fuselage and the relative rotor along the direction of extension of the relative wing.
B64C 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
B64D 35/04 - Transmitting power from power plant to propellers or rotors; Arrangements of transmissions characterised by the transmission driving a plurality of propellers or rotors
B64D 35/08 - Transmitting power from power plant to propellers or rotors; Arrangements of transmissions characterised by the transmission being driven by a plurality of power plants
B64C 27/22 - Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
A helicopter is described comprising: a tail boom; a fin projecting from the tail boom; and a tailplane arranged at the tail boom and transversal to the fin; at least one of the fin and the tailplane defining a first aerodynamic surface generating a first aerodynamic force; at least one first element transversal to the first aerodynamic surface; and a second aerodynamic surface generating a second aerodynamic force, connected to the first element, facing and spaced from the first aerodynamic surface; the second aerodynamic surface is spaced from the other of the fin and the tailplane.
B64C 27/82 - Rotorcraft; Rotors 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
A convertiplane is described that comprises a fuselage, having a first longitudinal axis, with a nose and a tail portion; a pair of wings arranged on respective opposite sides of said fuselage, carrying respective rotors; a pair of engines operatively connected to respective said rotors; at least one first lifting surface arranged on said tail portion; and a pair of canards arranged on said nose of said fuselage and defining respective second lifting surfaces adapted to generate a third lift/negative lift value; each rotor comprising a mast rotatable about a second axis and about an relative third axis transversal to said second axis and with respect to the fuselage, so as to set said convertiplane between a helicopter configuration and an aeroplane configuration; each second axis, in use, being transversal to the first axis of said convertiplane in said helicopter configuration and being parallel to said first axis in said aeroplane configuration.
B64D 27/24 - Aircraft characterised by the type or position of power plant using steam, electricity, or spring force
B64D 29/00 - Power-plant nacelles, fairings, or cowlings
B64D 35/04 - Transmitting power from power plant to propellers or rotors; Arrangements of transmissions characterised by the transmission driving a plurality of propellers or rotors
B64D 35/08 - Transmitting power from power plant to propellers or rotors; Arrangements of transmissions characterised by the transmission being driven by a plurality of power plants
B64D 27/02 - Aircraft characterised by the type or position of power plant
A method is described for the folding of a convertiplane with a fuselage having a first axis , a pair of wings and a pair of rotors arranged on respective mutually opposite sides of the respective wings; each rotor comprises a mast rotatable about a second axis and a plurality of blades; each wing comprises a first portion fixed with respect to the fuselage; a second tip portion opposite to the first portion; and a third intermediate portion, which is interposed between the associated first portion and second tip portion; the mast of each rotor is integrally tiltable with the second axis and associated second tip portion about a third axis transversal to the second axis and the fuselage so as to set said convertiplane between a helicopter configuration and an aeroplane configuration; the method comprises the steps i) of arranging the convertiplane in the helicopter configuration and ii) rotating a pair of assemblies of respective wings with respect to the fuselage and the associated first portion about respective fifth axes , so as to arrange the convertiplane in a stowage configuration. A convertiplane is also disclosed.
Closure system for connecting two contiguous transport units in a convoy for the transport of goods, the closure system comprising an accordion-shaped element configured to change the length thereof along a longitudinal axis of the convoy and comprising a central portion and a pair of outer portions placed on opposite sides with respect to said axis, the thickness of the accordion-shaped element decreasing from the central portion to the outer portions.
B65G 17/06 - Conveyors having an endless traction element, e.g. a chain, transmitting movement to a continuous or substantially-continuous load-carrying surface or to a series of individual load-carriers; Endless-chain conveyors in which the chains form the load-carrying surface having a load-carrying surface formed by a series of interconnected, e.g. longitudinal, links, plates, or platforms
F16C 29/08 - Arrangements for covering or protecting the ways
B65G 17/34 - Individual load-carriers having flat surfaces, e.g. platforms, grids, forks
A handle for opening and closing a door of an aircraft is provided. The handle has a base part lockable to a rotatable shaft of an opening mechanism of the door, a hand gripping part connected to the base part, and a hinge connecting the base part to the hand gripping part to allow relative rotation of the hand gripping part with respect to the base part about a first axis. At least one seat is integral with the base part and at least one seat is integral with the hand gripping part, the seats being adjacent and aligned along a second axis parallel to the first axis. A mechanical fuse element of constraint is received in the seats, such that by applying to the hand gripping part a bending stress around the hinge greater than a predetermined threshold, the mechanical fuse element of constraint shears between the seats.
A Multi-Beam on Receive Electronically Steerable Antenna comprising a Tx array comprising a phased array of Tx antenna elements and having a geometric aperture with one or more pairs of parallel opposite sides; and an Rx array comprising a phased array of Rx antenna elements and having a geometric aperture with one or more pairs of parallel opposite sides. One or more pairs of parallel opposite sides of the geometric aperture of the Tx array are inclined relative to one or more pairs of parallel opposite sides of the geometric aperture of the Rx array.
H01Q 3/34 - Arrangements for changing or varying the orientation or the shape of the directional pattern of the waves radiated from an antenna or antenna system varying the distribution of energy across a radiating aperture varying the phase by electrical means
An anti-torque rotor is described comprising: a mast rotatable about a first axis; a plurality of blades rotatable about respective second axes; an element slidable along the first axis with respect to the mast, rotating integrally with the mast and operatively connected to the blades; a control rod slidable along axis; a first bearing with a first ring rotating integrally with element, a second ring radially internal to the first ring with respect to the first axis and a plurality of first rolling bodies; a third ring sliding integrally with the control rod along the first axis and angularly fixed with respect to the first axis; and a locking element arranged in a standard configuration, in which it prevents the relative rotation of the second and third rings and movable from the standard 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 - Rotorcraft; Rotors 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
A system for evaluating an operator in a training mission on a training element, including a first processing unit configured to receive and process first data to generate converted data according to an operating frequency; a second processing unit configured to receive and process the converted data and mission support data according to the operating frequency to generate second data; and a third processing unit configured to receive and compare the converted data with the second data according to the operating frequency such to generate, based on said comparison, response data. Response data comprise visualisation data and the evaluation system further includes a graphic process unit configured to receive visualisation data and generate a map of the operating environment wherein the training element operates.
G09B 9/24 - Simulators for teaching or training purposes for teaching control of vehicles or other craft for teaching control of aircraft, e.g. Link trainer including display or recording of simulated flight path
An anti-torque rotor is described that comprises: a mast rotatable about a first axis; a plurality of blades extending along respective second axes; a control element sliding along the first axis with respect to the mast, integrally rotatable with said mast, and connected to said blades; a control rod sliding axially along first axis and angularly fixed with respect to said first axis; a connection element interposed between the control rod and the control element, sliding along the first axis integrally with the control rod, and configured to enable the relative rotation of said control element with respect to the control rod about the first axis; and a transmission unit available in an active configuration or an inactive configuration; the transmission unit, in turn, comprises: an annular ridge axially and angularly integral with the control rod and radially projecting from the control rod; and a seat engaged by the ridge and angularly integral with the control element.
B64C 27/78 - Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement in association with pitch adjustment of blades of anti-torque rotor
B64C 27/82 - Rotorcraft; Rotors 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
An aircraft capable of vertical take-off and landing is described, comprising a first propulsion unit configured to generate a first thrust directed along a first axis; a second propulsion unit configured to generate a second thrust directed along a second axis; the first propulsion unit and the second propulsion unit can be operated independently of one another; the first axis and second axis are inclined to one another with respect to a first longitudinal direction of the aircraft; the first axis and the second axis are fixed with respect to the aircraft.
A rotor for a hover-capable aircraft includes an attenuating device to attenuate the transmission of vibrations from a mast to the aircraft. The attenuating device includes a first mass free to oscillate parallel to a hub rotation axis with respect to a casing of the attenuating device and elastically connected to the casing. The attenuating device further includes a second mass free to oscillate parallel to the hub rotation axis, connection means adapted to make the first and second masses integrally movable along the hub rotation axis when the angular speed of the mast assumes a first value, and actuator means activatable to decouple the first and second masses when the angular speed of the mast assumes a second value, different from the first value.
An apparatus for carrying out load testing on an aircraft part is described. In one aspect, the apparatus includes means for constraining the aircraft part and a linear actuator for applying a test load. The linear actuator has a first part being tiltable and being pivotally constrained about a first and a second geometrical axes, orthogonal to one another, and a second part being slidably mounted on the first part to slide along a longitudinal direction. A load cell, mounted on the second part, measures force acting on the aircraft part along the longitudinal direction. In one aspect, a first clinometer and a second clinometer are mounted on the linear actuator, each clinometer measuring a respective angle representative of rotation of the linear actuator respectively about the first and second geometrical axes. A displacement transducer measures sliding of the second part relative to the first part of the linear actuator.
G01M 5/00 - Investigating the elasticity of structures, e.g. deflection of bridges or aircraft wings
G01B 11/14 - Measuring arrangements characterised by the use of optical techniques for measuring distance or clearance between spaced objects or spaced apertures
A rotor for an aircraft is described that has a mast, an attenuating device to attenuate the transmission of vibrations from the mast in a plane orthogonal to the first axis, and a transmission device interposed between the mast and the attenuating device; the attenuating device comprises a first and a second mass unit with a first and a second mass rotatable about the first axis with a first and a second rotational speed, two control units operable to cause an additional rotation of at least one of the first and second masses, and a first and a second support assembly carrying the first and second masses; each control unit controls the angle between the first and second masses and comprises a set of drive gear teeth integral with the first support assembly, a cogwheel with a set of control gear teeth meshing with the drive gear teeth, and an actuator to cause the rotation of the cogwheel about a second axis and of the first mass about said first axis.
A rotor for an aircraft is described that has a mast, an attenuating device to attenuate the transmission of vibrations from the mast in a plane orthogonal to the first axis; and a transmission device interposed between the mast and the attenuating device; the attenuating device comprises a first and a second mass unit with a first and a second mass rotatable about the first axis with a first and a second rotational speed, two control units operable to cause an additional rotation of at least one of the first and second masses; and a first and a second support assembly carrying the first and second masses; each control unit controls the angle between the first and second masses and each control unit comprises: a belt coupled to the support assembly and a drive unit coupled to the first belt, to cause the rotation of the first support assembly with respect to said transmission device.
A system includes a movable assembly configured for pushing a piece of ammunition into a breech ring of a firearm and/or closing the breech ring, under control of a motor. A feeding device is configured for feeding the piece of ammunition into a position situated between the movable assembly and the breech ring. A synchronization device co-operates with the motor on one side and with the feeding device on the other side. The synchronization mechanism provides for selective transmission of motion, under control of the movable assembly, from the motor to the feeding mechanism, when the movable assembly is in a position away from the breech ring.
F41A 9/02 - Feeding of unbelted ammunition using wheel conveyors, e.g. star-wheel-shaped conveyors
F41A 7/10 - Drives for externally-powered guns, i.e. drives for moving the breech-block or bolt by an external force during automatic firing using a rotating cylindrical drum having a camming groove
F41A 9/51 - Boosters, i.e. externally-powered motors
45.
METHOD FOR MANUFACTURING A SOUND-ABSORBING SANDWICH PANEL FOR REDUCING NOISE OF AN AIRCRAFT ENGINE
A method for manufacturing a sound-absorbing panel with a sandwich structure for reducing noise impact of an aeronautic engine includes providing a first skin of a thermoplastic polymeric material, making a plurality of micro-holes through the first skin by mechanical punching of the first skin, securing the first skin to a central layer by arranging a structural adhesive layer between the first skin and the central layer and/or by a thermal weld between the first skin and the central layer, and securing the central layer to a second skin by arranging a structural adhesive layer between the central layer and the second skin and/or by a thermal weld between the central layer and the second skin.
B64D 33/02 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
B29D 99/00 - Subject matter not provided for in other groups of this subclass
B32B 3/12 - Layered products essentially comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products essentially having particular features of form characterised by a discontinuous layer, i.e. apertured or formed of separate pieces of material characterised by a layer of regularly-arranged cells whether integral or formed individually or by conjunction of separate strips, e.g. honeycomb structure
B32B 7/12 - Interconnection of layers using interposed adhesives or interposed materials with bonding properties
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
B32B 37/12 - Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by using adhesives
B32B 3/26 - Layered products essentially comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products essentially having particular features of form characterised by a layer with cavities or internal voids
A breechblock assembly for a firearm includes a guiding element having a slide adapted to slide along a guide in an actuation system of the breechblock assembly driven by a motor. A shutting element shuts an opening in a breech ring of the firearm. A percussion pin is pushed by an elastic element slide along a longitudinal axis, as a function of the firing cycle of the firearm to an axial hole in the shutting element. The percussion pin is shaped to partially come out of the axial hole of the shutting element for firing a piece of ammunition. The breechblock assembly comprises a control system for controlling the percussion pin. The control system controls the operability and the movement of the percussion pin independently of a firing cycle of the firearm.
F41A 7/10 - Drives for externally-powered guns, i.e. drives for moving the breech-block or bolt by an external force during automatic firing using a rotating cylindrical drum having a camming groove
F41A 17/64 - Firing-pin safeties, i.e. means for preventing movement of slidably-mounted strikers
47.
Aircraft with tail portion having convergent and divergent winglets and related manufacturing method
An aircraft is described that comprises: a fuselage with a first axis of longitudinal extension; and a tail portion arranged at a tail end of the fuselage; the tail portion comprises two surfaces arranged in a V-shape, inclined to each other and symmetrical with respect to the first axis; each surface comprises an associated winglet arranged transversely with respect to the surface and fixed with respect to the surface.
An aircraft is described comprising: a support element; a shaft rotating about an axis; a pair of oblique rolling bearings mounted so as to couple the shaft to the support element rotatingly about the axis; the rolling bearings comprising: respective first races cooperating radially in contact with a first component defined by one from the support element and the shaft; respective second races cooperating radially in contact with a second component defined by the other from the support element and the shaft; and respective pluralities of rolling elements adapted to roll on the first and second races; the aircraft further comprises a pair of preloaded elastic members, which couple the first races to the first component respectively, axially and in an elastically yielding manner.
B64D 35/00 - Transmitting power from power plant to propellers or rotors; Arrangements of transmissions
B64C 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
F16C 19/18 - Bearings with rolling contact, for exclusively rotary movement with bearing balls essentially of the same size in one or more circular rows for both radial and axial load with two or more rows of balls
F16C 19/54 - Systems consisting of a plurality of bearings with rolling friction
F16C 25/08 - Ball or roller bearings self-adjusting
Convertiplane comprising a fuselage; a pair of wings, a pair of nacelles fixed with respect to the wings, and a pair of rotors rotatable about respective second axes and tiltable about a third axis between a first position, reached when the convertiplane is in an aeroplane configuration, and a second position, reached when the convertiplane is in a helicopter configuration. The wing comprises a wing box and a first appendage movable when the convertiplane is in the aeroplane configuration, between a first neutral position, a second raised operating position, and a third lowered operating position; the wing comprises a second appendage movable between a first neutral position assumed when the convertiplane is in the aeroplane configuration and in which it defines an extension of the wing box, and a second position assumed when the convertiplane is in the helicopter configuration and in which it defines, with the wing box, an opening through which the downwash generated by the rotor can flow.
A wing having a wing box (20) defining a first wing profile with a first leading edge, a first trailing edge, a first top surface and a first bottom surface; a first appendage hinged on the wing box and defining a second wing profile, in turn comprising an end wall and a second trailing edge, a second top surface and a second bottom surface; the first appendage is movable between: a first position, in which the first and the second wing profiles are contiguous with each other and a second position, in which the second bottom surface and second top surface are respectively separated from the first bottom surface and first top surface; the wing box comprises a first spar having a curved section in a plane orthogonal to the associated first axis; the end wall is curved and arranged abutting against the first spar at least along the second top surface and the second bottom surface when the first movable appendage is in the first position.
B64C 13/30 - Transmitting means without power amplification or where power amplification is irrelevant mechanical using cable, chain, or rod mechanisms
B64C 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
B64D 29/02 - Power-plant nacelles, fairings, or cowlings associated with wings
B64C 27/52 - Tilting of rotor bodily relative to fuselage
An anti-torque rotor is described comprising: a mast rotatable about a first axis; a plurality of blades hinged on the mast and rotatable about respective second axes to vary the respective angles of attack; a control element sliding along the first axis with respect to the mast, rotatable with the mast and connected to the blades to cause the rotation about the second axes; a control mechanism, axially sliding and angularly fixed with respect to the mast; and a connection element interposed between the control mechanism and the control element, sliding integrally with the control mechanism along the mast; the control mechanism comprises a first and a second rod; the rotor comprises a coupling, which is configured to enable/prevent rotation of the second rod with respect to the first rod when the torque exerted by the first connection element on the second rod about the first axis is greater/less than a threshold value in the event of failure of the connection element.
B64C 27/59 - Transmitting means, e.g. interrelated with initiating means or means acting on blades mechanical
B64C 27/82 - Rotorcraft; Rotors 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
52.
COMPOSITE MATERIAL AND METHOD FOR PRODUCING THE SAME
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 fan is described with a first conveying element, fluidly connectable with a source of a primary air flow and defining a first passage for the primary air flow; a first mouth receiving a first aliquot of the primary air flow from the first passage; a first Coanda surface onto which the first mouth directs the first aliquot; and a first opening fluidly connected with the first mouth and crossable by the first aliquot coming of the first mouth and a secondary air flow; the fan comprises a second conveying element, fluidly connected with the first conveying element and defining internally a second passage for a second aliquot of the primary air flow, and comprises: a second mouth receiving the second aliquot from the second passage and a second Coanda surface onto which the second mouth directs the second aliquot.
F04F 5/16 - Jet pumps, i.e. devices in which fluid flow is induced by pressure drop caused by velocity of another fluid flow the inducing fluid being elastic fluid displacing elastic fluids
The invention concerns a suborbital space traffic control system that comprises: a radar system configured to monitor a predetermined suborbital region and detect and track objects in the predetermined suborbital region. The objects include vehicles and space debris; and a suborbital space traffic monitoring system configured to: receive, from the radar system, tracking data related to the objects detected and tracked by the radar system; monitor, on the basis of the tracking data, trajectories of the objects in the predetermined suborbital region using one or more predetermined machine-learning techniques to detect potentially hazardous situations for the vehicles in the predetermined suborbital region; and, if it detects a potentially hazardous situation for one or more given vehicles, transmit corresponding alarm messages to the given vehicle(s).
B64G 1/24 - Guiding or controlling apparatus, e.g. for attitude control
B64G 3/00 - Observing or tracking cosmonautic vehicles
G01S 13/72 - Radar-tracking systems; Analogous systems for two-dimensional tracking, e.g. combination of angle and range tracking, track-while-scan radar
G01S 13/933 - Radar or analogous systems, specially adapted for specific applications for anti-collision purposes of aircraft or spacecraft
55.
Vertical take-off and/or landing aircraft and method for controlling a flow of a fluid along a fluidic line of a vertical take-off and/or landing aircraft
A vertical take-off and/or landing aircraft comprising: a fuselage having a longitudinal axis; a pair of semi-wings protruding from the fuselage in a transversal direction with respect to the longitudinal axis; a pair of a predetermined breaking areas of the semi-wings defining respective preferred rupture sections at which the respective semi-wings are designed to break, during operation, in a controlled way moving along a preferred collapse trajectory in the event of impact; and at least one fluidic line configured to convey at least one service fluid from and/or towards at least one said semi-wing and crossing at least one of said preferred rupture sections; the aircraft comprises a self-sealing coupling movable between a first configuration in which it enables the flow of said service fluid from and/or towards the semi-wing, and a second configuration in which it prevents the above-mentioned flow and the spilling of the service fluid from the fluidic line; the self-sealing coupling is movable from the first to the second configuration via the movement of the semi-wing along the preferred collapse trajectory.
An aerial, marine or land vehicle comprising: a compartment to be cooled; a first circuit through which can pass and, in turn, comprising, a heat exchanger that can be fed with the coolant and is designed to enable the coolant to release heat; a second circuit that can be fed with a second flow of a heat-carrying fluid and is thermally coupled to the heat exchanger; and supply means for supplying a mixture comprising water, inside the second flow in a position upstream of the heat exchanger and spaced from the heat exchanger, proceeding along the feed direction of the second flow along the second circuit, so as to cause evaporation of the mixture and cool the second flow in the heat exchanger.
B64D 13/08 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned the air being heated or cooled
A rotor is described that comprises: a hub; a plurality of blades; each blade extends along an axis and comprises: a leading edge and a trailing edge; a top surface and a bottom surface, a chord joining points of the leading edge and the trailing edge; and a closed shell made of composite material and adapted to withstand the torque directed along a first axis of the blade; the shell comprises a first and a second element separate from each other, delimiting the respective shell on mutually opposite sides; a first connection element arranged on the side of the associated leading edge and interposed between the first ends of the respective first and second elements; and a third element connected to the associated first and second elements and arranged on the side of the leading edge; the first connection element is connected to respective first faces, and the third element is connected to respective second faces of the first and second elements; the blade comprises a fourth element interposed between the fourth element and the first connection element.
A hover-capable aircraft is described that comprises a drive unit, a rotor and a transmission interposed between the drive unit and the rotor; the transmission comprises a gear; the gear, in turn, comprises a main body rotatable about a first axis and a plurality of first teeth projecting in a cantilever fashion from the main body; the gear comprises a first pair of first rings axially opposite to each other and cooperating with the gear so as to exert a radial force on the gear.
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
F16C 23/08 - Ball or roller bearings self-adjusting
A blade for a rotor of a hover-capable aircraft is described comprising: a main body with a first outer surface; and a de-icing system for removing ice; the de-icing system, in turn, comprises: a first layer formed by a shape-memory material activatable so as to alter its shape according to a temperature-associable quantity, which is arranged on at least one outer surface of the main body; the de-icing system is characterized in that it comprises a second covering layer, which defines at least a portion of a second outer surface of the blade on which ice deposits; the second layer laid on top of the first layer on the opposite side of the main body is selectively movable under the action of the first layer so as to exert a mechanical action on the ice and remove it from the blade, and is adapted to protect the first layer from external agents.
B64D 15/16 - De-icing or preventing icing on exterior surfaces of aircraft by mechanical means, e.g. pulsating mats or shoes attached to, or built into, surface
An electronic tool monitoring system to monitor usage and wear of tools for mechanical machining, comprising, for each tool to be monitored, a tag with a unique identifier and a self-contained, stand-alone electronic monitoring device. The electronic monitoring device comprises: an electronic sensory arrangement; an electronic communication interface; an electronic operator; and an electronic control unit. The electronic communication interface and the electronic operator interface are programmed to store data indicative of a service life of the tool, identify and monitor usage and wear of the tool based on an output of the electronic sensory arrangement, and estimate residual service life of the tool based on monitored usage and wear of the tool and the stored data indicative of service life of the tool. The system will implement certain actions based on whether the service life of the tool is determined to be exhausted.
B23Q 17/09 - Arrangements for indicating or measuring on machine tools for indicating or measuring cutting pressure or cutting-tool condition, e.g. cutting ability, load on tool
An anti-torque rotor is described for a helicopter, comprising: a mast rotatable about a first axis; a plurality of blades hinged on the mast, extending along respective second axes transversal to said first axis and rotatable about respective said second axes to alter the respective angles of attack; a control element sliding and rotating with respect to the mast, and operatively connected to said blades to cause the rotation of said blades about respective second axes following a translation of said element along the first axis; a control rod sliding axially along first axis with respect to the mast and angularly fixed with respect to the first axis; and a bearing interposed between the control rod and the control element, sliding along the first axis with respect to the mast and integrally with the control rod; the anti-torque rotor further comprises an interface made of an antifriction material interposed between said control rod and said bearing.
B64C 27/82 - Rotorcraft; Rotors 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 27/605 - Transmitting means, e.g. interrelated with initiating means or means acting on blades mechanical including swash plate, spider or cam mechanisms
62.
BOX-SHAPED MONOLITHIC STRUCTURE IN COMPOSITE MATERIAL FOR FUSELAGES AND WINGS OF AIRCRAFT AND METHOD FOR MANUFACTURING SAID STRUCTURE
The invention relates to a method for manufacturing a box-shaped monolithic structure with a cavity by curing a fiber-reinforced prepreg material. The method comprises using two or more elongated and internally hollow support tools which have a complementary form to that of the cavities to be manufactured, and a composition based on reinforcement material and polymer suitable to allow the passage from a rigid state to a flexible elastomeric state and vice versa in response to heating/cooling down. In the rigid state, the support tools allow the direct lamination of the prepreg material on their external walls and are configured to set the flexible elastomeric state at a temperature lower than the curing temperature and higher than 50° C. During the curing operation, the curing pressure is applied both outside the structure being formed and inside the support tools, whose walls have become flexible, to push on the prepreg material to be cured.
B64C 3/26 - Construction, shape, or attachment of separate skins, e.g. panels
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
63.
Rotor for a hover-capable aircraft and related method of control
A rotor for a hover-capable aircraft is described that comprises: a hub rotatable about a first axis and at least two blades hinged to the hub; each blade comprises a main portion hinged to the hub and a tip portion, which is arranged radially outermost with respect to first axis with respect to the corresponding main portion; the tip portion of each blade is movable with respect to the corresponding main portion of that blade; the tip portion of each blade is selectively movable with respect to the corresponding main portion of that blade between a first position, in which it defines a dihedral or anhedral angle with respect to the corresponding main portion; and a second position, in which it defines a positive or negative sweep angle with respect to the corresponding main portion.
A rotor for a hover-capable aircraft is described that comprises: a hub rotatable about a first axis and at least two blades hinged to the hub; each blade comprises a main portion hinged to the hub and a tip portion, which is arranged radially outermost with respect to first axis with respect to the corresponding main portion; the tip portion of each blade is movable with respect to the corresponding main portion of that blade; the tip portion of each blade is selectively movable with respect to the corresponding main portion of that blade between a first position, in which it defines a dihedral or anhedral angle with respect to the corresponding main portion; and a second position, in which it defines a positive or negative sweep angle with respect to the corresponding main portion.
A tail sitter aircraft includes a wing with a closed front section and a fuselage, from which the wing extends. The wing includes a first portion projecting from the fuselage and a second portion spaced from the first portion. The aircraft includes first and second connecting section that are interposed between the first and second portions. The fuselage extends parallel to a first axis and the first and second portions extend parallel to a second axis orthogonal to the first axis. The first axis is arranged, in use, vertically in a take-off/landing position and inclined with respect to the vertical direction in a cruising position.
B64C 29/02 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis vertical when grounded
B64C 9/00 - Adjustable control surfaces or members, e.g. rudders
B64C 25/32 - Alighting gear characterised by elements which contact the ground or similar surface
B64C 27/54 - Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement
B64C 39/02 - Aircraft not otherwise provided for characterised by special use
B64C 39/06 - Aircraft not otherwise provided for having disc- or ring-shaped wings
A tail sitter aircraft is described that comprises: a fuselage arranged vertically in a take-off/landing position and transversely to a vertical direction in a cruising position of the aircraft; a single wing; at least two first engines configured to exert respective first thrusts directed along respective first axes on the tail sitter; and at least two second engines rotating about respective second axes arranged above said first axes of the first engines, with reference to the cruising position; the at least two second engines being configured to exert respective second thrusts directed along respective second axes on the tail sitter; the first and second engines being carried by the single wing; the single wing comprises a first portion and a second portion mutually staggered from one another; the second portion being arranged above said first portion, with reference to said cruising position; said first portion comprises two half-wings, extending from opposite lateral sides of the fuselage; the wing further comprises a third portion arranged below said first portion with reference to said cruising position of said aircraft.
B64C 29/02 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis vertical when grounded
B64C 27/54 - Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement
B64C 39/02 - Aircraft not otherwise provided for characterised by special use
B64C 39/06 - Aircraft not otherwise provided for having disc- or ring-shaped wings
B64D 27/02 - Aircraft characterised by the type or position of power plant
B64D 31/00 - Power plant control; Arrangement thereof
A convertiplane is described that has a fuselage with a first axis, a pair of half-wings, and a pair of rotors arranged on mutually opposite ends of the half-wings. The rotor comprises a mast hinged on a second axis and a plurality of blades hinged on the mast. The mast of the rotor can be tilted with the second axis about a third axis transversal to the second axis and with respect to the fuselage to transform the convertiplane between a helicopter mode and an aeroplane mode; the second axis is transversal to the first axis in the helicopter mode and is parallel to the first axis in the aeroplane mode. The rotor disc can be tilted about a fourth axis. The rotor comprises control means for controlling the cyclic pitch and collective pitch of the blades comprising: a first actuator controllable to vary the collective pitch, a second actuator controllable to vary the tilt of the rotor disc about the fourth axis and a rod movable to alter the tilt of the corresponding rotor disc about a fifth axis according to the mode of the convertiplane.
An emergency exit for a helicopter is described that comprises: a wall defining an opening; a removable part engaging the opening in a removable manner; and a seal interposed between the wall and the removable part. The seal is transformable between: a first configuration, in which it prevents removal of the removable part from the wall following application of a predetermined load on the removable part; and a second configuration, in which it allows removal of the removable part from the wall following application of the predetermined load on the removable part. The emergency exit comprises an insert interposed between the seal and the wall; at least one of the insert and the seal comprise at least one tooth engaging a recess with a shape corresponding to the tooth and defined by the other of the insert and said seal, when the seal keeps, in use, the removable part constrained to wall.
A heat exchanger for a transmission unit of an aircraft is described that comprises: a first module defining a first feed path for a first fluid to be cooled; a second module defining a second feed path for a second cooling fluid; the first and second feed paths being thermally coupled to each other; each second module comprising: at least one cell formed by an inlet for a second cooling fluid; an outlet for the second cooling fluid, which is arrange on the opposite side to the inlet along a first direction; a first wall thermally coupled to the first path; a pair of second walls; and a plurality of fins projecting in a cantilever fashion from the first wall. The heat exchanger further comprises at least a first row of fins, which lie on a plane orthogonal to the first direction, the fins of the first row extending at progressively increasing distances from one of the second walls along a second direction orthogonal to the first direction.
F02C 7/14 - Cooling of plants of fluids in the plant
F28D 9/00 - Heat-exchange apparatus having stationary plate-like or laminated conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall
F28D 21/00 - Heat-exchange apparatus not covered by any of the groups
71.
Method and tool for manufacturing a composite aircraft window frame
The invention relates to a method for manufacturing a composite aircraft window frame; the method comprises the steps of: a) positioning in a mold a preform made of pre-impregnated material including dispersed fibers, with a predefined orientation, in a thermosetting resin matrix; b) closing the mold so as to define a gap between at least one surface of said preform and a portion of said mold; c) injecting thermosetting resin into the closed mold through an inlet opening of the mold itself, so as to fill the gap and completely lap said surface of the preform; and d) applying a uniform hydrostatic pressure on the surface by the injection of the resin.
B29C 70/48 - 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 and impregnating the reinforcements in the closed mould, e.g. resin transfer moulding [RTM]
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 45/14 - Injection moulding, i.e. forcing the required volume of moulding material through a nozzle into a closed mould; Apparatus therefor incorporating preformed parts or layers, e.g. injection moulding around inserts or for coating articles
B64F 5/10 - Manufacturing or assembling aircraft, e.g. jigs therefor
B29C 70/20 - Fibrous reinforcements only characterised by the structure of fibrous reinforcements using fibres of substantial or continuous length oriented in a single direction, e.g. roving or other parallel fibres
B29K 105/08 - Condition, form or state of moulded material containing reinforcements, fillers or inserts of continuous length, e.g. cords, rovings, mats, fabrics, strands or yarns
B29L 31/30 - Vehicles, e.g. ships or aircraft, or body parts thereof
72.
Compression molding device of parts in composite material starting from plates in composite with a thermoplastic matrix
A compression molding device configured for the production of a part in composite material starting from a plate in composite with a thermoplastic matrix is described. The device comprises: a fixed support structure; an upper half-die provided with a first contoured surface corresponding to the profile of an upper surface of the part to be made; a lower half-die provided with a second contoured surface corresponding to the profile of a lower surface of the part to be made; holding means carried by the support structure and configured to hold the plate in a position interposed between the half-dies; and moving means for moving at least one of the half-dies from and towards the plate. The holding means comprise two or more releasable grippers gripping by friction distinct portions of the peripheral edge of the plate and configured to completely release or allow the complete release of the plate.
B29C 43/36 - Moulds for making articles of definite length, i.e. discrete articles
B29C 43/02 - Compression moulding, i.e. applying external pressure to flow the moulding material; Apparatus therefor of articles of definite length, i.e. discrete articles
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
73.
Process for obtaining carbon dioxide from furnace combustion fumes
A process for obtaining carbon dioxide from furnace combustion fumes is provided. The process comprises removing water vapour occurring in combustion fumes through successive gas compression and expansion steps; separating carbon dioxide from oxygen and nitrogen through the use of a filter comprising a gas-separating material, including fullerenes and zeolites, to obtain substantially pure gaseous carbon dioxide; subsequently optionally producing dry ice through further steps of compression and expansion of the substantially pure gaseous carbon dioxide obtained in the preceding steps.
B01D 53/14 - Separation of gases or vapours; Recovering vapours of volatile solvents from gases; Chemical or biological purification of waste gases, e.g. engine exhaust gases, smoke, fumes, flue gases or aerosols by absorption
B01D 53/00 - Separation of gases or vapours; Recovering vapours of volatile solvents from gases; Chemical or biological purification of waste gases, e.g. engine exhaust gases, smoke, fumes, flue gases or aerosols
B01D 5/00 - Condensation of vapours; Recovering volatile solvents by condensation
B01D 53/92 - Chemical or biological purification of waste gases of engine exhaust gases
74.
Acoustic system for detecting and locating low intensity and low frequency sound sources and related locating method
An acoustic system and method detect and locate low intensity and low frequency sound sources in an investigation area. An acoustic system is effective in identifying survivors trapped under rubble following a catastrophic event. The acoustic system focuses on the low frequency components of the human voice and includes acoustic sensors for detecting acoustic signals generated by the sound sources and for generating data representative of the acoustic signals. A wireless transmitter transmits the data representative of the detected acoustic signals to an electronic receiver block that receives and analyzes the data. A processor executes calibration of the acoustic sensors of the suite to temporally align each signal received from the acoustic sensors, and executes a digital beamforming to combine the data representative of the detected acoustic signals and to create an acoustic image of the investigation area to locate the low intensity and low frequency sound sources.
H04R 1/40 - Arrangements for obtaining desired frequency or directional characteristics for obtaining desired directional characteristic only by combining a number of identical transducers
G01S 5/30 - Determining absolute distances from a plurality of spaced points of known location
G01S 3/82 - Direction-finders for determining the direction from which infrasonic, sonic, ultrasonic, or electromagnetic waves, or particle emission, not having a directional significance, are being received using ultrasonic, sonic, or infrasonic waves with means for adjusting phase or compensating for time-lag errors
G10K 11/34 - Sound-focusing or directing, e.g. scanning using electrical steering of transducer arrays, e.g. beam steering
Multilayer radar-absorbing laminate for aircraft made of polymer matrix composite material with graphene nanoplatelets, and method of manufacturing same
A multilayer radar-absorbing laminate includes three juxtaposed blocks.
A first electrically conductive block is arranged toward the inside of the aircraft in use.
A second electromagnetic intermediate absorber block has a layer of electrically non-conductive fiber sheets is permeated by graphene-based nanoplatelets to achieve a periodic and electromagnetically subresonant layer, the conductive layers containing graphene nanoplatelets alternating with non-conductive layers.
A third block of electrically non-conductive material is arranged towards the outside and forms part of the outer surface of the aircraft. The second block is produced by depositing on the fiber sheets a suspension of graphene nanoplatelets in a polymeric mixture, with controlled penetration of the graphene nanoplatelets into the fiber sheets. A plurality of dry fiber sheets sprayed with the suspension of graphene nanoplatelets is superimposed. An unpolymerized thermosetting synthetic resin is infused into a lay-up made of the first, second and third blocks. Afterwards, the thermosetting resin is polymerized.
B32B 27/12 - Layered products essentially comprising synthetic resin next to a fibrous or filamentary layer
B29C 70/02 - Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising combinations of reinforcements and fillers incorporated in matrix material, forming one or more layers, with or without non-reinforced or non-filled layers
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
B32B 17/04 - Layered products essentially comprising sheet glass, or fibres of glass, slag or the like in the form of fibres or filaments bonded with or embedded in a plastic substance
C08J 5/24 - Impregnating materials with prepolymers which can be polymerised in situ, e.g. manufacture of prepregs
B82Y 30/00 - Nanotechnology for materials or surface science, e.g. nanocomposites
B82Y 40/00 - Manufacture or treatment of nanostructures
A kit for a helicopter is described, the helicopter comprising a fuselage and a rotor; the kit comprises at least one device adapted to dampen the vibrations transmitted from the rotor to the fuselage and to be interposed between the fuselage and the rotor; the device, in turn, comprises a first threaded element operatively connectable to the rotor and adapted to, in use, vibrate parallel to a first axis; a second threaded element operatively connectable to the fuselage and operatively connected to the first threaded element so as to, in use, rotationally vibrate about the first axis; and a plurality of threaded rollers, which are screwed on the first and second threaded elements; the rollers being rotatable about their respective second axes parallel to and separate from the first axis with respect to the first and second threaded elements; the rollers are also rotatable about the first axis with respect to the first threaded element and the second threaded element.
F16F 7/10 - Vibration-dampers; Shock-absorbers using inertia effect
F16F 15/02 - Suppression of vibrations of non-rotating, e.g. reciprocating, systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating system
F16H 25/22 - Screw mechanisms with balls, rollers, or similar members between the co-operating parts; Elements essential to the use of such members
A kit is described that comprises a device adapted to dampen the vibrations transmitted by the rotor to the fuselage; the device comprises two first elements movable along a first axis; two second elements rotatable about the first axis; a first inerter with a first female screw, a first screw, and first rollers rotatable about respective second axes and around the first axis with respect to the first female screw and first screw; a second inerter with a second female screw, a second screw operatively connected to the second female screw; and a plurality of second rollers rotatable about second axes and around the first axis with respect to the second female screw and second screw; the first and second female screws defining the first threaded elements, and the first and second screws defining the second threaded elements; or the first and second screws defining the first threaded elements and the first and second female screws defining the second threaded elements.
An anti-torque system (10) for a helicopter (1) is described that comprises: an electric power supply unit (15); at least one first rotor (17), operatively connected to an electric power supply unit (15) and operable by the electric power supply unit (15) so as to rotate with a first variable angular speed; and at least one second rotor (25) operatively connected to electric power supply unit (15) and operable by the electric power supply unit (15) so as to rotate with a second variable angular speed.
B64C 27/82 - Rotorcraft; Rotors 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
A rotor for a hover-capable aircraft is described, comprising: a hub rotatable about an axis and, in turn, comprising a plurality of blades; a mast connectable to a drive member of the aircraft and operatively connected to the hub to drive the hub in rotation about the axis; and damping means for damping vibrations transmitted to the mast, which comprise a mass designed to oscillate in a plane transversal to the axis so as to contain flexural vibrations of the mast generated by rotation of the blades; the damping means also comprise elastic means having a desired stiffness along the axis and operatively connected to the mass to contain vibration of the mast along the axis.
Valve system for an electrochemical power supply source, in particular for an underwater vehicle, and corresponding electrochemical power supply source
An electrochemical-type power supply source is provided with: an electrochemical stack generating electric power, in the presence, internally, of electrolytic fluid, provided with a number of distinct groups of galvanic cells and of a corresponding number of electrolyte inlet pipes for introducing electrolyte into respective groups of galvanic cells and with electrolyte outlet pipes for extracting electrolyte from respective groups of galvanic cells; a main tank, fluidically coupled to the electrochemical stack and containing electrolytic fluid; and a recirculation system, defining a circulation path of the electrolytic fluid between the main tank and the electrochemical stack. A valve system that can be coupled to the electrolyte inlet and/or outlet pipes and operatively controllable to modify hydraulic and electric characteristics of the circulation path, in response to a power delivery condition by the power supply source.
H01M 50/00 - Constructional details or processes of manufacture of the non-active parts of electrochemical cells other than fuel cells, e.g. hybrid cells
H01M 50/77 - Arrangements for stirring or circulating the electrolyte with external circulating path
F42B 19/24 - Propulsion specially adapted for torpedoes by electric motors
H01M 10/42 - Methods or arrangements for servicing or maintenance of secondary cells or secondary half-cells
H01M 50/60 - Arrangements or processes for filling or topping-up with liquids; Arrangements or processes for draining liquids from casings
H01M 50/691 - Arrangements or processes for draining liquids from casings; Cleaning battery or cell casings
81.
High efficiency electrochemical power supply source for an underwater vehicle
An electrochemical-type power supply source for use in marine environment, is provided with: an electrochemical stack, which generates electric power in the presence, internally, of an electrolytic fluid; a first tank, designed to contain electrolytic fluid at a first temperature; a second tank, designed to contain electrolytic fluid at a second temperature, lower than the first temperature; a thermostatic valve, that mixes electrolytic fluid at a lower temperature with electrolytic fluid at a higher temperature, for generating a mixed electrolytic fluid to be introduced into the electrochemical stack at a controlled temperature for generating a desired electric power. The electrochemical power supply is further provided with an auxiliary tank, adapted to contain electrolytic fluid at a third temperature, higher than the first temperature; and the thermostatic valve is connected to the auxiliary tank and receives, at an input, the electrolytic fluid at the third temperature.
G05D 11/16 - Controlling mixing ratio of fluids having different temperatures, e.g. by sensing the temperature of a mixture of fluids having different viscosities
G05D 23/13 - Control of temperature without auxiliary power by varying the mixing ratio of two fluids having different temperatures
82.
Centrifugal separator of gas—liquid for electrochemical battery
A centrifugal gas-liquid separator wherein a tubular casing houses a central tubular duct, which is provided with a first free end and with a second end that communicates with a gas-outlet duct and carries a transversal annulus-shaped plate having a perimetral edge that faces the inner wall of the tubular body to define an annular gap. The plate divides the space inside the tubular casing into a first chamber and into a second chamber that communicate with each other through the annular gap. A liquid-outlet duct communicates with the second chamber and a liquid-phase/gas-phase inlet duct extends tangentially from the tubular casing and discharges into the first chamber through an inlet nozzle. A regulation device is provided, which is designed to modify the section of the inlet nozzle in order to modify the rate of entry of the liquid phase and gas phase into the first chamber and to adapt the operation of the centrifugal gas-liquid separator following variations of flow rate.
B04C 3/06 - Construction of inlets or outlets to the vortex chamber
B01D 45/12 - Separating dispersed particles from gases or vapours by gravity, inertia, or centrifugal forces by centrifugal forces
B01D 45/16 - Separating dispersed particles from gases or vapours by gravity, inertia, or centrifugal forces by centrifugal forces generated by the winding course of the gas stream
H01M 8/04276 - Arrangements for managing the electrolyte stream, e.g. heat exchange
H01M 8/18 - Regenerative fuel cells, e.g. redox flow batteries or secondary fuel cells
B04C 3/00 - Apparatus in which the axial direction of the vortex remains unchanged
B04C 11/00 - Accessories, e.g. safety or control devices, not otherwise provided for
B01D 50/00 - Combinations of methods or devices for separating particles from gases or vapours
B04C 5/13 - Construction of the overflow ducting, e.g. diffusing or spiral exits formed as a vortex finder and extending into the vortex chamber; Discharge from vortex finder otherwise than at the top of the cyclone; Devices for controlling the overflow
A47L 9/16 - Arrangement or disposition of cyclones or other devices with centrifugal action
83.
Stability and command augmentation system for an aircraft, and stabilization and control method of an aircraft
A stability and command augmentation system for controlling an aircraft, comprising: a first member moveable by a pilot input device to a first position defining a first input; a second member moveable to a second position associated with a second input; and an adder device configured to add the first and second inputs and supply an output signal defining a command for an element to be controlled of the aircraft; the stability and command augmentation system comprises: a casing, a first and a second piston integrally movable with one another inside the casing and operatively connected to the second member; and control means configured to exert a first force on the first piston and a second force on the second piston; the second force is independent of the first force.
B64C 13/30 - Transmitting means without power amplification or where power amplification is irrelevant mechanical using cable, chain, or rod mechanisms
B64C 13/40 - Transmitting means with power amplification using fluid pressure
B64C 13/50 - Transmitting means with power amplification using electrical energy
F15B 18/00 - Parallel arrangements of independent servomotor systems
G05G 11/00 - Manually-actuated control mechanisms provided with two or more controlling members co-operating with one single controlled member
84.
Geometric and radiometric calibration and test apparatus for electro-optical thermal-IR instruments and designed to simulate different angularly-extending thermal-IR sources with different geometries and with thermal-IR emissions containing different hot-cold transitions
A geometric and radiometric calibration and test apparatus for electro-optical thermal-IR (8-12 micron) instruments and designed to simulate angularly-extending thermal-IR sources with different geometries and with thermal-IR emissions containing hot-cold transitions. The apparatus comprises an IR collimator having an optical axis and a focal plane; a thermal-IR source movable relative to the collimator to be controllably arrangeable and displaceable in the focal plane of the collimator, and operable to radiate thermal-IR radiations towards the collimator; and a kit of masks interchangeably arrangeable in front of the thermal-IR source and having geometric and radiometric properties to cause the thermal-IR radiation reproduced on the electro-optical instrument to be calibrated or tested to contain different hot-cold transitions.
A safety auxiliary system, coupled to a modular battery of an underwater vehicle having a number of modules, each provided with a plurality of cells, has: a first subsystem, which detects conditions indicative of a thermal runaway in any of the modules d manages such a thermal runaway, intervening locally on the module to cool the corresponding cells so that the thermal runaway is not propagated; and a second subsystem, cooperating with, and operatively coupled to, the first subsystem, which manages gases present in the module associated with the thermal runaway, preventing them from pouring inside the underwater vehicle. The first subsystem is provided with a first electronic control unit for each of said modules, and the second subsystem is provided with a second electronic control unit, distinct from, and operatively coupled to, the first electronic control unit through a communication connection, so as to receive an alarm signal upon detection of the conditions indicative of the thermal runaway in the corresponding module.
B60L 50/60 - Electric propulsion with power supplied within the vehicle using propulsion power supplied by batteries or fuel cells using power supplied by batteries
B60L 58/26 - Methods or circuit arrangements for monitoring or controlling batteries or fuel cells, specially adapted for electric vehicles for monitoring or controlling batteries for controlling the temperature of batteries by cooling
H01M 10/0525 - Rocking-chair batteries, i.e. batteries with lithium insertion or intercalation in both electrodes; Lithium-ion batteries
H01M 10/42 - Methods or arrangements for servicing or maintenance of secondary cells or secondary half-cells
H01M 10/48 - Accumulators combined with arrangements for measuring, testing or indicating the condition of cells, e.g. the level or density of the electrolyte
H01M 50/20 - Mountings; Secondary casings or frames; Racks, modules or packs; Suspension devices; Shock absorbers; Transport or carrying devices; Holders
H01M 50/375 - Vent means sensitive to or responsive to temperature
Door for cargo airplane, wherein a cargo compartment is accessible from the outside of the fuselage through an opening for loading goods provided with the door. The door is provided with a first operating handle accessible from the outside of the door and used to lock/unlock the pins that are used to connect the door to the fuselage and control the closing/opening of a ventilation door; and a second operating handle accessible from the outside of the door for advancing/retracting the pins in/from respective seats. According to the invention, the door is provided with a third handle accessible from the inside of the door and mechanically interconnected with the first handle for locking/unlocking the pins and controlling the closing/opening of the ventilation door; and a fourth operating handle accessible from the inside of the door and mechanically interconnected with the second handle for advancing/retracting the pins in/from respective seats.
Described herein is a safety valve for a hydraulic circuit comprising a pump designed to supply a hydraulic fluid at a first pressure value to a pressure line, comprising: a chamber, which can be fluidically connected to the pressure line and is filled with the hydraulic fluid at a pressure value and a temperature value; and a casing with an opening, which can be connected to a reservoir of the hydraulic circuit; a shutter, which delimits the first chamber and can be displaced between a first position, in which it occludes the first opening, and a second position, in which it leaves the opening at least in part free; the valve comprises a thermally expandable element, which can be displaced, as a result of the temperature of the hydraulic fluid, between a first configuration that it assumes when the temperature of the hydraulic fluid is below the threshold value and a second configuration that it assumes when the temperature of the hydraulic fluid is above the temperature threshold value and in which it holds or displaces the first shutter in or towards the second position so as to reduce the pressure in the first chamber.
A rotor for an aircraft is described that comprises: a hub rotatable about an axis and, in turn, comprising a plurality of blades; a mast connectable to a drive member of the aircraft and connected to the hub to drive the hub in rotation about the axis; and damping means to dampen the transmission of vibrations to the mast in a plane orthogonal to the axis; the damping means comprising at least a first mass and a second mass that can eccentrically rotate about the axis with a first and a second speed of rotation, respectively; the first mass and second mass are operatively connected to the mast to generate, respectively, a first and a second damping force on the mast having a main component in a direction radial to the axis; the rotor comprises a transmission unit, which is interposed between the mast and the first and second masses so as to drive the first and second masses in rotation.
F16H 1/06 - Toothed gearings for conveying rotary motion without gears having orbital motion involving only two intermeshing members with parallel axes
F16H 1/16 - Toothed gearings for conveying rotary motion without gears having orbital motion involving only two intermeshing members with non-parallel axes comprising worm and worm-wheel
F16H 1/28 - Toothed gearings for conveying rotary motion with gears having orbital motion
89.
Electromagnetic induction welding device for joining composite materials and relative joining method
A portable welding device comprising: a base facing a work surface, designed to receive tapes in electrically conductive composite materials to be joined or defined by at least one already positioned tape; an operating head receiving one tape at a time and movable with respect to the base along at least a first movement line parallel to the work surface; a motorized arm connecting the operating head to the base and selectively activatable to impart movements to the operating head; and feeding means selectively activatable to feed one tape at a time to the operating head and connected to the operating head; the operating head comprises a positioning roller receiving a tape at a time; a pressure roller spaced from and aligned with the positioning roller along the first movement line; and an inductor interposed between the positioning roller and the pressure roller with reference to the first movement line.
B29C 65/00 - Joining of preformed parts; Apparatus therefor
B29C 65/36 - Joining of preformed parts; Apparatus therefor by heating, with or without pressure using heated elements which remain in the joint, e.g. "verlorenes Schweisselement" heated by induction
A method for manufacturing a wing box for aircraft comprises the steps of arranging, on a curing surface, a first panel of composite material, alternately arranging, on the first panel, along a transverse direction, a rib of non-polymerized composite material and a tool comprising a central part, a bottom part and a top part, wherein the central part of each tool is interposed between said bottom part and the top part and may be extracted in a transverse direction, arranging a second panel of composite material by putting said second panel in contact with the flanges of each rib, pulling out the central part of each tool along the transverse direction and removing the top part and the bottom part of each tool, and subjecting the first panel, the second panel, and each rib to a curing process in autoclave with vacuum bag.
B64F 5/00 - Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
B29C 33/00 - SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING - Details thereof or accessories therefor
B29D 99/00 - Subject matter not provided for in other groups of this subclass
B64C 3/26 - Construction, shape, or attachment of separate skins, e.g. panels
B64F 5/10 - Manufacturing or assembling aircraft, e.g. jigs therefor
B29C 33/48 - SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING - Details 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
B29L 31/30 - Vehicles, e.g. ships or aircraft, or body parts thereof
91.
Method for manufacturing a multi-ribbed wing-box of composite material with integrated stiffened panels and communicating bays
A method for manufacturing a wing-box for aircraft comprises: arranging, on a curing surface, a first panel of composite material comprising a skin a plurality of longitudinal stringers, and arranging, on each stringer, a caul plate; arranging, on the first panel, pluralities of support inserts so that each support insert rests on a respective caul plate, and on the skin of the first panel, and arranging, on the first panel, a plurality of ribs of non-polymerized composite material, each rib comprising a plate, a first pair of flanges and a second pair of flanges arranged at opposed ends of the plate, and having openings on an edge of the plate, by placing the respective first pair of flanges on the first panel and the respective plurality of openings on the plurality of support inserts, and having the first panel and the plurality of ribs undergo a curing process in autoclave with vacuum bag.
B32B 3/00 - Layered products essentially comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products essentially having particular features of form
B32B 7/00 - Layered products characterised by the relation between layers; Layered products characterised by the relative orientation of features between layers, or by the relative values of a measurable parameter between layers, i.e. products comprising layers having different physical, chemical or physicochemical propert; Layered products characterised by the interconnection of layers
B32B 37/00 - Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding
B64F 5/10 - Manufacturing or assembling aircraft, e.g. jigs therefor
B32B 3/08 - Layered products essentially comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products essentially 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 7/12 - Interconnection of layers using interposed adhesives or interposed materials with bonding properties
B32B 37/10 - Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the pressing technique, e.g. using direct action of vacuum or fluid pressure
B32B 37/12 - Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by using adhesives
A rotor for an aircraft capable of hovering includes a stationary support structure and a rotative element which is rotatable about an axis with respect to the stationary support structure. The rotor has at least one blade, which is operatively connected with a rotative element. The rotor has a source of a magnetic field, which is either stationary or driven in rotation at a first rotational speed and an electric conductive element, which is operatively connected to the rotative element and can be driven in rotation at a second rotational speed different from first rotational speed. An electric conductive element is electromagnetically coupled so that an electromotive force is magnetically induced in electric conductive element itself Two rings extend radially inward from a tubular body of the rotor hub with the first ring connected to a plurality of thermally conductive rings of a flow deflector at an axial end of the rotor and the second ring supports the electric conductive element.
B64C 27/82 - Rotorcraft; Rotors 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
B64D 15/12 - De-icing or preventing icing on exterior surfaces of aircraft by electric heating
F16H 1/46 - Systems consisting of a plurality of gear trains, each with orbital gears
93.
Method for performing diagnostics of a structure subject to loads based on the measurement of displacements and system for implementing said method
A method for performing diagnostics of a structure subject to loads, in particular an aircraft structure, is described, said method being implemented by means of an arrangement of sensors located at relevant points of the structure and corresponding neural networks, and comprising: training the neural network in order to establish an associative relationship between the local displacement of the structure in a subset of relevant points and the local displacement of the structure in at least one residual relevant point; detecting the local displacement of the structure in a plurality of relevant points under operating conditions; estimating the local displacement of the structure in at least one residual relevant point by means of the associated neural network on the basis of the pre-established associated relationship; and comparing the local displacement of the estimated structure with the detected local displacement at the residual relevant point.
A rotor for an aircraft capable of hovering includes a stationary support structure and a rotative element, which is rotatable about a first axis with respect to said stationary support structure with a first rotational speed. The rotor includes at least one blade, which is operatively connected with said rotative element; and a transmission group, which includes an output element rotatable about first axis with a second rotational speed different from first rotational speed.
A fuze for an explosive weapon, comprising onboard sensors to monitor operation of the fuze and/or the explosive weapon, a radar sensor to transmit radar signals and receive reflected radar signals, and an electronic signal processor connected to the onboard sensors and to the radar sensor and programmed to implement a main operating function aimed at implementing a detonation logic, and a secondary operating function supplemental to the main one and comprising a telemetry function designed to determine, based on signals from the onboard sensors, and to transmit, via the radar sensor, telemetry data indicative of the operation of the fuze and/or the explosive weapon during flight thereof.
F42C 13/04 - Proximity fuzes; Fuzes for remote detonation operated by radio waves
F42C 13/00 - Proximity fuzes; Fuzes for remote detonation
96.
Certifiable deterministic system software framework for hard real-time safety-critical applications in avionics systems featuring multi-core processors
An avionics system comprising a central processing unit to implement one or more hard real-time safety-critical applications, the central processing unit comprises a multi-core processor with a plurality of cores, an avionics system software executable by the multi-core processor, a memory, and a common bus though which the multi-core processor can access the memory; the avionics system is characterized in that the avionics system software is designed to cause, when executed, the cores in the multi-core processor to access the memory through the common bus by sharing bus bandwidth according to assigned bus bandwidth shares.
There is disclosed a rotor for an aircraft capable of hovering, comprising: a stator; a rotatable element, which is rotatable about an axis with respect to stator; a blade, which is connected with element; a support element, which supports a source of a magnetic field and is either stationary or driven in rotation at a first rotational speed; and a first electric circuit, which is angularly integral with element and can be driven in rotation at a second rotational speed different from first rotational speed; first electric circuit being electromagnetically coupled with source so that an electromotive force is magnetically induced in first electric circuit and an first electric current flows in first electric circuit; rotor further comprises a second electric circuit which is either stationary or driven in rotation at a first rotational speed, and a sensor generating a signal associated to a back electromotive force induced on second electric circuit.
B64C 27/68 - Transmitting means, e.g. interrelated with initiating means or means acting on blades using electrical energy, e.g. having electrical power amplification
H02K 16/02 - Machines with one stator and two rotors
An ice-breaking system for an aircraft, comprising a pneumatic ice-breaking device, an air inlet adapted to receive air from the environment outside the aircraft and an air outlet adapted to discharge air into the outside environment, and a motorized valve having an air loading port connected to the air inlet and an air discharge port connected to the air outlet, the valve being configured to supply air to the pneumatic ice-breaking device in a pulsating way. When the aircraft is in motion, the kinetic energy of the air at the air inlet and originating from the relative motion between the air and the aircraft is converted into air pressure at the pneumatic ice-breaking device, and the air outlet is positioned so that when the aircraft is in motion the air pressure at the air outlet is lower than the outside ambient pressure.
B64D 15/16 - De-icing or preventing icing on exterior surfaces of aircraft by mechanical means, e.g. pulsating mats or shoes attached to, or built into, surface
F16K 11/074 - Multiple-way valves, e.g. mixing valves; Pipe fittings incorporating such valves; Arrangement of valves and flow lines specially adapted for mixing fluid with all movable sealing faces moving as one unit comprising only sliding valves with pivoted closure members with flat sealing faces
patents
