Abstract

The artefact comprises a flat or curved body substantially made of metal or metal alloy or composite material and comprising one or more ice protection panel(s). The ice protection panel(s) comprise a heater film and at least one ply made of CFRC and/or GFRC. The heater film includes a thermoplastic polymeric matrix containing polar groups, and at least one graphene or graphitic layer which is electrically conductive, or a thermosetting resin, and functionalized with elastomeric nanodomains containing dispersed electrical conductive carbon–based nanoparticles. The heater film is also provided of electrodes and is placed between said at least one ply made of CFRC and/or GFRC and an outer protective coating, or is placed between two plies independently made of CFRC and/or GFRC.

IPC Classes  ?

• H05B 3/14 - Heating elements characterised by the composition or nature of the materials or by the arrangement of the conductor characterised by the composition or nature of the conductive material the material being non-metallic
• B64D 15/12 - De-icing or preventing icing on exterior surfaces of aircraft by electric heating
• H05B 3/34 - Heating elements having extended surface area substantially in a two-dimensional plane, e.g. plate-heater flexible, e.g. heating nets or webs

Abstract

Aircraft (1) capable of hovering comprising a fuselage (2), at least one rotor (3a, 3b, 4) that is rotatable with respect to the fuselage (2), electrical drive means adapted to rotate the rotor (3a, 3b, 4) and electrically powered by a battery (9), and a cooling system (10) of the battery (9). Said cooling system (10) comprises, in turn, a first opening (20) for the air to enter, second openings (21) for the air to escape and a passage (22), which places the first opening (20) in fluidic communication with the second openings (21) and within which the battery (9) is placed. The cooling system (10) further comprises a fan (23) adapted to increase the kinetic energy of the air contained in the passage (22) and which is operated when the forward speed (v) of the aircraft (1) with respect to the ground is lower than a speed threshold value (v0) and/or when the temperature (T) of the battery (9) exceeds a temperature threshold value (T0).

IPC Classes  ?

• B64D 33/08 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
• B64D 27/24 - Aircraft characterised by the type or position of power plant using steam, electricity, or spring force
• B64D 13/00 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space
• B64C 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
• B64C 27/28 - Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with forward-propulsion propellers pivotable to act as lifting rotors
• B64D 13/06 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned

Abstract

The turret, in particular for naval applications, comprises a traversing part and an elevating part integrally rotatable with the traversing part. There is a barrel supported by the elevating part and integrally rotatable therewith about the elevation axis (X1). The barrel is configured to fire guided ammunition through itself. An ammunition guidance system (24) is configured to direct a guided piece of ammunition towards a target by means of an electromagnetic emission. A moving device (100), whereon the ammunition guidance system (24) is mounted, is configured to move the latter in such a way as to orient the electromagnetic emission towards the target. The moving device (100) is mounted to the traversing part (14) and comprises a frame (102) that rotatably supports the ammunition guidance system (24) about an azimuthal or traversing movement axis (Y1) and a zenithal or elevation movement axis (X1).

IPC Classes  ?

• F41G 3/22 - Aiming or laying means for vehicle-borne armament, e.g. on aircraft
• F41G 7/26 - Optical guidance systems
• F41G 7/28 - Radio guidance systems
• F41G 5/14 - Elevating or traversing control systems for guns for vehicle-borne guns
• F41G 5/20 - Elevating or traversing control systems for guns for vehicle-borne guns for guns on ships
• F41A 23/00 - Gun mountings, e.g. on vehicles; Disposition of guns on vehicles

Abstract

Fire fighting drone comprising an exoskeleton (2) defining an internal space (3) extending along an axis H and a flexible bag (4) stably housed in the internal space (3), provided with a release valve (6) and configured to contain a fire fighting liquid (7); a support structure (8) provided with a plurality of thrusters (11) adapted to perform a thrust that enables the support structure (8) to be supported in flight; the support structure (8) is connected to a first end portion (2-a) of the exoskeleton (2); a plurality of movable directional wings (10) carried by the exoskeleton (2), extending outwards from the exoskeleton itself and angularly movable relative to the exoskeleton (2) around respective axes H transverse to the axis H; an electronic control unit adapted to control the thruster (11), to generate the release signal and adapted to control the actuators that perform the rotation of the wings; the electronic control unit is configured to control said wings to allow the rotation of the wings during the free-fall phase of said drone which is released from an aircraft and thereby performs a certain trajectory of said drone from the aircraft to a launch zone; the electronic unit is configured to enable the discharge of said liquid from said bag and the activation of the thrusters (11) following the discharge of the liquid to enable the flight of the support structure and of the exoskeleton containing the empty bag to a landing zone.

IPC Classes  ?

• B64D 1/16 - Dropping or releasing powdered, liquid or gaseous matter, e.g. for fire-fighting

Abstract

The turret (10), in particular for naval applications, comprises a traversing part (14) and an elevating part (16) integrally rotatable with the traversing part (14). There is a barrel (18) supported by the elevating part (16) and integrally rotatable therewith about the elevation axis (X). The barrel (18) is configured to fire guided ammunition through itself. An ammunition guidance system (24) is configured to direct a guided piece of ammunition towards a target by means of an electromagnetic emission. A protection device (26) is provided, which is configured to assume a closing condition, wherein it encloses and protects the ammunition guidance system (24), and an opening condition, wherein it clears and exposes the ammunition guidance system (24). The ammunition guidance system (24) and the protection device (26) are mounted to the traversing part (14). The traversing part (14) internally defines a reclosable cavity (28) that houses the ammunition guidance system (24), faces forwards, and is configured to be closed by the protection device (26) when the latter is in the closing condition.

IPC Classes  ?

• F41A 23/24 - Turret gun mountings
• F41H 5/013 - Mounting or securing armour plates
• F41H 5/16 - Shields for ordnance
• F41H 5/20 - Turrets
• F41H 7/04 - Armour construction
• F41A 23/20 - Gun mountings, e.g. on vehicles; Disposition of guns on vehicles for disappearing guns

Abstract

An aircraft (1) comprising a fuselage (2, 2', 2'') with a nose (4) and a tail (5) arranged on opposite parts to each other along a first longitudinal axis (Y) is described; a pair of half-wings (3) arranged on respective mutually opposite sides of the fuselage (2, 2', 2'); a first and a second rotor (22a, 22b) carried by respective half-wings (3), respectively rotatable around a second and third axis (F, G) inclinable with respect to said fuselage (2, 2', 2''), and independently operable from each other; the aircraft (1) is switchable between a first hovering flight or take-off/landing configuration wherein the fourth and fifth axis (F, G) are arranged orthogonal to said first axis (Y); and a second forward flight configuration wherein the fourth and fifth axis (F, G) are arranged parallel or inclined with respect to said first axis (Y); the aircraft (1) further comprising a tail portion (6) comprising a first aerodynamic surface (8), and a third and a fourth rotor (21a, 21b) rotatable around a fixed fourth and a fifth axis (D, E); and support means (31a, 31b) of the third and fourth rotor (21a, 21b) connected to a corresponding said half-wing (3) and to a corresponding said fin (52).

IPC Classes  ?

• B64C 39/04 - Aircraft not otherwise provided for having multiple fuselages or tail booms
• B64C 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
• B64C 39/08 - Aircraft not otherwise provided for having multiple wings
• B64C 39/12 - Canard-type aircraft

Abstract

A fuselage (2, 2', 2'') for a convertible aircraft (1) is described, comprising a nose (4) and a tail (5) arranged on mutually opposite sides along a first longitudinal axis (Y) of the fuselage (2); a first portion (100) and a second portion (101) arranged one after the other, proceeding along the first axis (Y) from the nose (4) towards the tail (5); and an electric power source (102) connectable with at least one electric powertrain (40a, 40b, 40c, 40d, 40e, 40f) and arranged inside the second portion (101); the first and second portion (100, 101) define respectively a first and a second section (110, 111, 111'') in a plane orthogonal to the first axis (Y); the second section (111) defines at least one air intake (120) that is open towards the outside of the fuselage (2) itself and fluidically connected with the source (102) so as to convey, in use, a flow of cooling air onto the source (102) itself following the forward motion of the aircraft (1); the second section (111, 111'') having a larger area than the first section (110); the air intake (120) being arranged at a sidewall (19) of the second portion (101) and externally to the first portion (100) and in a view parallel to the first axis (Y).

IPC Classes  ?

• B64D 27/24 - Aircraft characterised by the type or position of power plant using steam, electricity, or spring force
• B64D 33/08 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
• B64C 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
• B64C 7/00 - Structures or fairings not otherwise provided for
• B64C 1/14 - Windows; Doors; Hatch covers or access panels; Surrounding frame structures; Canopies; Windscreens
• B64C 1/00 - Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
• B64U 101/61 - UAVs specially adapted for particular uses or applications for transporting goods other than weapons for transporting passengers

Abstract

Method for identifying malfunction conditions of the sensors that measure the amount of fuel in the tanks of an aircraft (1) provided with at least one first tank (2/6) arranged on a first side of the aircraft and at least one second tank (4/8) arranged on a second side, each first and second tank (2/6; 4/8) is provided with a plurality m of sensors (11) detecting the level of fuel within the respective tank (2/6 and 4/8). The method performs a symmetry control wherein the level gradients (11) associated with the first tank (2/6) and the second tank (4/8) are compared to each other; and if the values of the compared gradients are close, a consistency condition is detected. As an alternative to the symmetry control, a discontinuity control is carried out wherein the step of comparing the consumption gradient associated with each sensor (11) with a reference gradient comprising an average consumption gradient of the other sensors and/or with the total consumption gradient is carried out.

IPC Classes  ?

• G01F 25/20 - Testing or calibration of apparatus for measuring volume, volume flow or liquid level or for metering by volume of apparatus for measuring liquid level
• B64D 37/00 - Arrangements in connection with fuel supply for power plant

Abstract

The invention relates to equipment (10) for making a structural element (1) of composite material having a longitudinal axis (A) and an axial cavity (2). The equipment (10) comprises a support frame (11) and a laminating mandrel (12), which is mounted on the support frame (11) so that it can rotate about its own central axis (B) and defines an outer laminating surface (13); the support frame (11) comprises two vertical headers (14, 15), facing each other and parallel to each other, and longitudinal connecting means (16) for longitudinally connecting the headers (14, 15); each header (14, 15) comprises a fixed portion (17) and a movable portion (18), coaxially receiving the laminating mandrel (12) and rotatable about the central axis (B) in relation to the fixed portion (17); the laminating mandrel (12) comprises a central shaft (26, 26' ), a plurality of sectors (30) angularly spaced apart about the central axis (B), and a plurality of linear actuators (31) extending between the central shaft (26, 26' ) and respective sectors (30) to move the sectors (30) themselves between an expanded laminating position and a contracted position; the equipment (10) further comprises first constraining means (35) for connecting in a releasable manner the sectors (30), arranged in the expanded laminating position, to the movable portions (18) of the headers (14, 15), and second constraining means (36) connecting the linear actuators (31) to the sectors (30) in a releasable manner so as to enable the extraction of the central shaft (26, 26' ) and linear actuators (31) from the equipment (10) in the condition in which the sectors (30), in the expanded position, are connected to the movable portions (18) of the headers (14, 15) by means of the first constraining means (35).

IPC Classes  ?

• B29C 70/32 - 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 on a rotating mould, former or core
• B29C 33/20 - Opening, closing or clamping
• 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
• B29D 99/00 - Subject matter not provided for in other groups of this subclass
• B64C 1/00 - Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
• B29C 70/54 - Component parts, details or accessories; Auxiliary operations

Abstract

12344) to the phase modulators (42); receive the detection signal (INT) from the optical sensor, indicative of an intensity of the sampled recombined beam; calculate a cost function (J) from the detection signal (INT), wherein the cost function is a function of the intensity of the sampled recombined beam; perform an optimization algorithm of the cost function, configured to maximise the intensity of the sample recombined beam; and provide a plurality of updated phase control signals, based on a result of the optimization algorithm.

IPC Classes  ?

• H01S 3/10 - Controlling the intensity, frequency, phase, polarisation or direction of the emitted radiation, e.g. switching, gating, modulating or demodulating
• H01S 3/13 - Stabilisation of laser output parameters, e.g. frequency or amplitude
• H01S 3/23 - Arrangement of two or more lasers not provided for in groups , e.g. tandem arrangement of separate active media
• G02B 6/42 - Coupling light guides with opto-electronic elements
• G02B 27/09 - Beam shaping, e.g. changing the cross-sectioned area, not otherwise provided for
• G02B 27/10 - Beam splitting or combining systems
• H01S 3/00 - Lasers, i.e. devices using stimulated emission of electromagnetic radiation in the infrared, visible or ultraviolet wave range
• H01S 3/067 - Fibre lasers

Abstract

Transmission assembly (3, 3', 3'', 3''' 3'''') for an aircraft (1) capable of hovering, comprising : a first and a second member (7, 8) and support means (9) of the first member (7) with respect to the second member (8); a primary lubrication circuit (20) comprising a primary tank (11) of a lubricating fluid and primary fluidic supply means (12) for supplying fluid to the support means (9); and an emergency lubrication circuit (22) comprising an emergency tank (23) of lubricating fluid fluidically connected to the primary tank (11); and auxiliary fluidic supply means (30) of the lubricating fluid to the support means (9), comprising a nozzle (24); the auxiliary fluidic supply means (30) comprise a dosing device (31, 31', 31'', 31''' 31'''') and a fluidic line (32), which fluidically connects the emergency tank (23) with the dosing device (31, 31', 31'', 31''' 31''''); the dosing device (31, 31', 31", 31''' 31'''') comprising a passage (33, 33'''') for the lubricating fluid from the fluidic line (32) to the nozzle (24), which comprises a plurality of concentrated pressure drop sections (6, 6''''), which are distinct and spaced apart from each other.

IPC Classes  ?

• F16H 57/04 - Features relating to lubrication or cooling

Abstract

A ground station for deliveries and pick-ups by a drone comprising a vertical structure (4) fixable to the ground or to a fixed structure and provided with an arm (5) movable between a rest position and an extended activation position wherein the arm (5) extends transversely in a cantilever fashion from the vertical structure (4); the vertical structure (4) carries a first marker Ml at the top that is designed to be recognised by the drone during flight to activate a step of approach of the drone to the ground station while maintaining a predetermined horizontal distance from the ground station and a first and a second laser emitter (8, 9) defining respectively a first /a second position reference for the drone wherein a portion (3f) of the drone has a first or a second vertical distance DI, D2 from the arm (5) arranged in the extended position; the ground station (2) is configured to carry out a coupling procedure of an end portion (5f) of the arm (5) with a support structure (11) of a load (12) carried by the drone (3).

IPC Classes  ?

• B64F 1/20 - Arrangement of optical beacons
• B64U 10/14 - Flying platforms with four distinct rotor axes, e.g. quadcopters
• A47G 29/14 - Deposit receptacles for food, e.g. breakfast, milk; Similar receptacles for large parcels with appliances for preventing unauthorised removal of the deposited articles
• B64C 39/02 - Aircraft not otherwise provided for characterised by special use
• B64U 101/60 - UAVs specially adapted for particular uses or applications for transporting goods other than weapons
• B64D 1/22 - Taking-up articles from earth's surface

Abstract

mast1mast2…mastNmast1mast2…mastNeng1eng2…engMCOLLCOL…COLLmastSYMeng1eng2…engMCOLLCOLL…COLLmastASYM1mastASYM2…mastASYMNCOLLCOLL2…COLLNCOLLCOL…COLLmast1mast2…mastNmastSYMmastASYM1mastASYM2…mastASYMNmastASYMN).

IPC Classes  ?

• B64C 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
• G05B 13/02 - Adaptive control systems, i.e. systems automatically adjusting themselves to have a performance which is optimum according to some preassigned criterion electric
• G05D 1/08 - Control of attitude, i.e. control of roll, pitch, or yaw
• B64D 31/00 - Power plant control; Arrangement thereof
• F02C 7/00 - Features, component parts, details or accessories, not provided for in, or of interest apart from, groups ; Air intakes for jet-propulsion plants

Abstract

prob prob (NUM_C, W) ) including, for each instant of time of the succession of instants of time, a corresponding probability vector (CX) including, for each class of a plurality of classes of manoeuvres, a corresponding estimate of the probability that, in the instant of time, the aircraft (1) has performed a manoeuvre belonging to the class; and selecting (123), for each instant of time of the succession of instants of time, a corresponding class of manoeuvres, based on the probability estimates of the corresponding probability vector (CX).

IPC Classes  ?

• G06N 20/00 - Machine learning
• G05B 23/02 - Electric testing or monitoring

Abstract

iiiiii'iiiii) indicative of the direction of the beam (20).

IPC Classes  ?

• G01B 11/16 - Measuring arrangements characterised by the use of optical techniques for measuring the deformation in a solid, e.g. optical strain gauge
• G01B 11/00 - Measuring arrangements characterised by the use of optical techniques
• G01S 17/66 - Tracking systems using electromagnetic waves other than radio waves
• G01S 17/14 - Systems determining position data of a target for measuring distance only using transmission of interrupted, pulse-modulated waves wherein a voltage or current pulse is initiated and terminated in accordance with the pulse transmission and echo reception respectively, e.g. using counters

Abstract

iiii). The processor (6) is adapted to normalize (14) the saliency maps (S, Si), resize (15) the normalized saliency maps (SNii Niii ↑) and the normalized saliency map (SNFF) on which to detect the object of interest.

IPC Classes  ?

• G06V 10/32 - Normalisation of the pattern dimensions
• G06V 10/46 - Descriptors for shape, contour or point-related descriptors, e.g. scale invariant feature transform [SIFT] or bags of words [BoW]; Salient regional features
• G06V 10/80 - Fusion, i.e. combining data from various sources at the sensor level, preprocessing level, feature extraction level or classification level
• G06V 20/52 - Surveillance or monitoring of activities, e.g. for recognising suspicious objects

Abstract

immmimimimimcciimcmm).

IPC Classes  ?

• G01C 23/00 - Combined instruments indicating more than one navigational value, e.g. for aircraft; Combined measuring devices for measuring two or more variables of movement, e.g. distance, speed or acceleration
• G06T 7/00 - Image analysis
• G06V 20/00 - Scenes; Scene-specific elements
• G09G 5/14 - Display of multiple viewports
• G06V 10/75 - Image or video pattern matching; Proximity measures in feature spaces using context analysis; Selection of dictionaries

Abstract

RLL) of a transparent region of the sky veil (SV) depends on a roll angle of the aircraft (2).

IPC Classes  ?

• G01C 23/00 - Combined instruments indicating more than one navigational value, e.g. for aircraft; Combined measuring devices for measuring two or more variables of movement, e.g. distance, speed or acceleration

Abstract

Communication system, comprising: a first data bus (2) configured to transport a first data signal according to a first transmission direction; a second data bus (2) configured to transport a second data signal according to a second transmission direction different from the first transmission direction; a synchronization bus (10); and a plurality of local resources (R1, R2) generating a respective local signal to be transmitted on the first and second data bus (2, 4). All transceivers are modulated with CDMA encoding and take place following a synchronism signal. The unidirectionality of transmission on the data buses 2, 4 guarantees the absence of interference. The communication system is fully scalable.

IPC Classes  ?

• G06F 13/42 - Bus transfer protocol, e.g. handshake; Synchronisation

Abstract

010121212121010101); a first summing element (23) that sums the first extracted signal and the second extracted signal, thereby generating the first error signal at the first output port; and a second summing element (24) that sums the third extracted signal and the fourth extracted signal, thereby generating the second error signal at the second output port.

IPC Classes  ?

• H01Q 13/02 - Waveguide horns

Abstract

A control unit (46, 46') for an aircraft (1, 1') capable of hovering or for a flight simulation system of the aircraft (1, 1') is described, the control unit (46, 46') is programmed to receive at input at least a first signal associated with real or simulated flight parameters (ALT, OAT; ALT', OAT') of the aircraft (1, 1') and to provide at output a second signal (VNE, VNE') associated with a forward velocity to never exceed of the aircraft (1, 1'); the control unit (46, 46') is programmed to process a third signal (GW, GW') associated with an actual or simulated weight of the aircraft (1, 1'); to associate plurality of tables (T1, T2,.., Tn) to respective intervals (I1, I2,.. Ij) of values of the third signal (GW, GW'); each table (T1, T2,.., Tn) associating a plurality of values of the second signal (VNE, VNE') with a respective first signal (ALT, OAT; ALT', OAT'; AEO, OEI, Power off; AEO', OEI', Power off'); and to process the second signal (VNE, VNE'), based on the table (T1, T2,.., Tn) associated with the relative interval (T1, T2,.. Ij) of the third signal (GW, GW') and the respective first signals (ALT, OAT; ALT', OAT').

IPC Classes  ?

• B64D 31/00 - Power plant control; Arrangement thereof
• G09B 9/08 - Simulators for teaching or training purposes for teaching control of vehicles or other craft for teaching control of aircraft, e.g. Link trainer
• G09B 19/16 - Control of vehicles or other craft
• B64D 43/00 - Arrangements or adaptations of instruments
• B64D 45/00 - Aircraft indicators or protectors not otherwise provided for
• B64C 27/00 - Rotorcraft; Rotors peculiar thereto
• G01C 23/00 - Combined instruments indicating more than one navigational value, e.g. for aircraft; Combined measuring devices for measuring two or more variables of movement, e.g. distance, speed or acceleration

Abstract

A control unit (46, 46') for an aircraft (1, 1') capable of hovering or for a flight simulation system of the aircraft (1, 1') is described; the control unit (46, 46') is programmed to: - receive in input a plurality of data associated with equipment (15) and/or kits (25) actually installed or simulated on the aircraft (1, 1') and/or with the operating configuration of the equipment (15) and/or kits (25); the equipment (15) and/or kits (25) causing a reduction of the actual or simulated forward velocity of the aircraft (1, 1'); - store a table (TX) defining a correspondence between each datum and a respective value of a first signal (Vmax, Vmax') associated with a value of maximum forward velocity of the aircraft (1, 1'); and - display the lowest of the first signals (Vmax, Vmax').

IPC Classes  ?

• B64D 45/00 - Aircraft indicators or protectors not otherwise provided for
• G01C 23/00 - Combined instruments indicating more than one navigational value, e.g. for aircraft; Combined measuring devices for measuring two or more variables of movement, e.g. distance, speed or acceleration
• B64D 43/00 - Arrangements or adaptations of instruments
• G09B 19/16 - Control of vehicles or other craft
• G09B 9/08 - Simulators for teaching or training purposes for teaching control of vehicles or other craft for teaching control of aircraft, e.g. Link trainer
• B64C 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
• B64C 27/04 - Helicopters

Abstract

Test device for an aeronautical component ( 2 ) wherein M low- energy impacts are performed on the component to be subjected to testing ( 2 ) by calculating the relative uncertainty Ui of the non-destructive tests. A destructive test (block 120 ) is performed on the aeronautical component ( 2 ) by measuring and storing the value of a quantity VI representative of the elastic stress applied to the component during the destructive test and based on this the uncertainty of the destructive test is calculated (block 130 ). The absolute value of the difference between target values of quantities Ci based on a theoretical model that describes the elastic behaviour of the component to be subjected to testing and the value of the quantity VI representative of the elastic stress applied to the component during the destructive test (ABS ( Ci -Vi ) ) is compared with the product of the uncertainty of the destructive test Al and a scaling factor k in order to certify the theoretical model as describing with sufficient accuracy the behaviour of the aeronautical component during the destructive test.

IPC Classes  ?

• G01M 7/08 - Shock-testing
• G01M 17/007 - Wheeled or endless-tracked vehicles
• G01N 3/34 - Investigating strength properties of solid materials by application of mechanical stress by applying repeated or pulsating forces generated by mechanical means, e.g. hammer blows

Abstract

A control device (50) for controlling the variation of the angle of attack of the blades (8) of the anti-torque rotor (4) for an aircraft (1) capable of hovering is described, comprising a control element (16) sliding along a first axis (A) with respect to a shaft (6) of the rotor (4) and rotatable integrally therewith; the control element (16) is operatively connected to a plurality of blades (8) articulated on the shaft (6) in order to vary the angle of attack thereof following a translation of the element (16) itself along the axis (A); a control rod (10) axially sliding along the axis (A) with respect to the shaft (6) and angularly fixed with respect to the axis (A); and a rolling bearing (17) interposed between the control rod (10) and the control element (16), sliding along the axis (A) with respect to the shaft (6) and integrally with the control rod (10); the control device (50) comprises a threaded element (51) screwed onto the control rod (10) and cooperating with the bearing (17) to constrain it axially with respect to the control rod (10) and a bushing (52) coupled in an angularly and axially fixed manner to the threaded element (51), and in an angularly fixed manner to the control rod (10).

IPC Classes  ?

• 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
• F16B 37/14 - Cap nuts; Nut caps or bolt caps
• F16B 39/08 - Locking of screws, bolts, or nuts in which the locking takes place after screwing down with a cap interacting with the nut, connected to the bolt by a pin or cotter-pin

Abstract

1NQ1NQik,iφkφk (t) ), the smoothed series of samples forming a smoothed unknown matrix (TFDMx' ); on the basis of the base functions, applying (206) to the smoothed unknown matrix and to the corresponding sets of coefficients a classifier trained to generate, for each flight regime among a plurality of flight regimes, a corresponding estimate of the probability that the smoothed unknown matrix and the corresponding sets of coefficients belong to a cluster relative to the flight regime; identifying (208) a flight regime in which the aircraft operated, on the basis of the estimates generated by the classifier.

IPC Classes  ?

• G05B 23/02 - Electric testing or monitoring

Abstract

A method of joining a first element (2) in composite material with a second element (3) in composite material to define a structural component (4) of an aircraft is described, the method comprises the steps of: a) arranging the first element (2) in contact on the second element (3); b) applying a non-rigid heating layer (6) on the first element (2); c) applying a layer of shape memory thermoplastic polymer ( 7 ), pre-loaded in a compressed non-equilibrium condition, onto the heating layer (6); d) applying a vacuum bag (8) to the assembly thus obtained; e) sealing the vacuum bag (8) to define a vacuum chamber (10) housing the first element (2), at least part of the second element (3), the heating layer (6) and the shape memory layer (7); f) applying vacuum inside the vacuum chamber (10); g) applying heat to the first element (2), to the second element (3) and to the shape memory layer (7) by activating the heating layer (6); h) expanding the shape memory layer (7) from the compressed non- equilibrium condition to an expanded equilibrium condition by means of the step g) of applying heat; 1) applying pressure to the first element (2) for compacting it against the second element (3) by means of the step h) of expanding.

IPC Classes  ?

• B29C 65/18 - Joining of preformed parts; Apparatus therefor by heating, with or without pressure using heated tool
• B29C 65/50 - Joining of preformed parts; Apparatus therefor using adhesives using adhesive tape
• B29C 73/12 - Apparatus therefor, e.g. for applying
• B29C 73/32 - Apparatus or accessories not otherwise provided for for local pressing or local heating using an elastic element, e.g. inflatable bag
• B29L 31/30 - Vehicles, e.g. ships or aircraft, or body parts thereof

Abstract

An aircraft window configured to reduce the intensity of vibrations transmitted from outside the aircraft to inside the aircraft cabin comprising: a first element of transparent material (2) arranged, in use, facing the outside of the aircraft; a second element of transparent material (3) arranged, in use, facing the cabin; a gap (4) that separates the first and second elements of transparent material (2,3) which are arranged facing and spaced apart from one another, a first transparent sheet element (5) applied to a first face of the first element (2) facing the gap; and at least one second transparent sheet element (7) applied to a second face of the second element (3) facing the gap. The first and second transparent sheet elements (5,7) are made of transparent viscoelastic material.

IPC Classes  ?

• B60J 1/00 - Windows; Windscreens; Accessories therefor
• B32B 17/00 - Layered products essentially comprising sheet glass, or fibres of glass, slag or the like
• B64C 1/14 - Windows; Doors; Hatch covers or access panels; Surrounding frame structures; Canopies; Windscreens

Abstract

Aircraft (1) comprising: a moving system (10) adapted for use when the aircraft (1) is in flight to move sensing means (18) of the aircraft between a rest position, wherein the sensing means (18) are arranged within the aircraft, and a work position, wherein the sensing means (18) face directly, along a sensing direction (y), toward the outside of the aircraft (1) and towards the ground when the aircraft (1) is in flight, comprising: a frame (12) arranged inside the aircraft (1); a slide (14), to support said sensing means (18); and a pair of guides (16), each comprising a rail part (16a), supported on said frame (12), and at least one draw part (16b; 16b') arranged telescopically slidable relative to the relevant rail part (16a) along a direction of movement (x) that is essentially perpendicular to said sensing direction (y); the slide (14) being mounted integrally with the draw parts (16b; 16b') of the pair of guides (16) in such a way to slide along the direction of movement (x) internally within the aircraft (1) to move said sensing means (18) between said rest position and said work position.

IPC Classes  ?

• B64D 43/00 - Arrangements or adaptations of instruments
• B64D 47/08 - Arrangements of cameras

Abstract

The illumination optical device (50) comprises a collimator (54), a light source (52), and an aperture (56). The collimator comprises a primary mirror (70A), a secondary mirror (70B), a tertiary mirror (70C) and a quaternary mirror (70D) mutually tilted so as to form a collimator optical path (80) extending between the light source and the aperture and formed, in succession, by the light source, the quaternary mirror, the tertiary mirror, the secondary mirror, the primary mirror and the aperture. The light source is configured to emit light rays, along respective directions, which form a main beam (63) propagating along directions intercepting the quaternary mirror so as to follow the collimator optical path; and a secondary beam (65) propagating along directions not intercepting the quaternary mirror. The illumination optical device is characterised in that the collimator comprises a shielding structure (100A-100E) configured to prevent illumination of the aperture by the secondary light beam.

IPC Classes  ?

• G02B 5/00 - Optical elements other than lenses
• G02B 27/00 - Optical systems or apparatus not provided for by any of the groups ,

Abstract

A locking device (1) for an aircraft is described, comprising a body (2) adapted to be fixed to a support surface (S), a first ring (3) and a second ring (4) rotatable the one with respect to the other with respect to a rotation axis (I) between a first angular position (61) and a second angular position (63). The first and second ring (3, 4) enclose an area (6) for the landing of the aircraft and are contained within the body (2). The locking device also comprises a plurality of cables (5), which connect the first ring (3) to the second ring (4). The locking device (1) is positionable in an unlocking position, wherein the first and second ring (3, 4) are in the first angular position (61), the cables (5) are spaced from said area (6); or in a locking position, wherein the first and second ring (3, 4) are in the second angular position (63) and the cables (5) occupy a region (63) of the area (6), so as to cooperate in contact with the aircraft to constrain it with respect to the support surface (S).

IPC Classes  ?

• B64F 1/00 - Ground or aircraft-carrier-deck installations
• B64F 1/12 - Anchoring

Abstract

The present invention relates to a system for generating light radiation to neutralize microorganisms. Said system comprises a light source (1 ) for emitting a light radiation, storage means (2) with one or more unique identification codes, each of which is associated with a respective microorganism, and at least one respective wavelength range associated with said microorganism, and a logic control unit (3). Said logic control unit (3) is configured to: o select a wavelength range based on the microorganism to be neutralized, o activate said light source (1) in such a way that the light radiation emitted by said light source (1) has a wavelength within said selected wavelength range, so that, when the system is in use, said light radiation induces an optical resonance in the microorganism, causing a denaturation of the genetic patrimony of said microorganism.

IPC Classes  ?

• A61L 2/10 - Ultraviolet radiation
• A61L 2/24 - Apparatus using programmed or automatic operation
• A61M 1/14 - Dialysis systems; Artificial kidneys; Blood oxygenators
• A61L 2/00 - Methods or apparatus for disinfecting or sterilising materials or objects other than foodstuffs or contact lenses; Accessories therefor
• A61L 2/08 - Radiation
• A61B 1/267 - Instruments for performing medical examinations of the interior of cavities or tubes of the body by visual or photographical inspection, e.g. endoscopes; Illuminating arrangements therefor for the respiratory tract, e.g. laryngoscopes, bronchoscopes
• A61B 1/06 - Instruments for performing medical examinations of the interior of cavities or tubes of the body by visual or photographical inspection, e.g. endoscopes; Illuminating arrangements therefor with illuminating arrangements
• A61B 1/273 - Instruments for performing medical examinations of the interior of cavities or tubes of the body by visual or photographical inspection, e.g. endoscopes; Illuminating arrangements therefor for the upper alimentary canal, e.g. oesophagoscopes, gastroscopes
• A61B 5/00 - Measuring for diagnostic purposes ; Identification of persons

Abstract

A method for manufacturing a core (10) for a panel (100) for an aircraft comprises the steps of: arranging first sheet-shaped partitioning elements (12), each having a plurality of vertical slits (16) extending transversely from a first edge thereof (12a), spaced from each other so that the distance between two successive first partitioning elements (12) is not constant; arranging second sheet- shaped partitioning elements (14), each with a plurality of vertical slits (16), extending transversely from one of its first edges (14a), on the first partitioning elements (12), transversely thereto, so that each vertical slit (16) of the second partitioning elements (14) interlocks with a respective vertical slit (16) of a respective first partitioning element (12), to define a plurality of cells (26) delimited laterally by a pair of opposing first partitioning elements (12) and a pair of opposing second partitioning elements (14).

IPC Classes  ?

• F02C 7/045 - Air intakes for gas-turbine plants or jet-propulsion plants having provisions for noise suppression
• F02K 1/44 - Nozzles having means, e.g. a shield, reducing sound radiation in a specified direction
• F02K 1/82 - Jet pipe walls, e.g. liners
• B64C 1/40 - Sound or heat insulation

Abstract

Method for manufacturing a core (10) for an aircraft panel (100) with the steps of: arranging first sheet-shaped partitioning elements (12), each with vertical slits (16), extending transversely from a first edge (12a), and transverse slits (22) extending transversely to the vertical slits (16), spaced from each other; arranging second sheet-shaped partitioning elements (14), each with vertical slits (16) extending transversely from a first edge (14a), on the first partitioning elements (12), transversely thereto, so that each vertical slit (16) of the second partitioning elements (14) interlocks with a respective vertical slit (16) of a respective first partitioning element (12), so that the first partitioning elements (12) and the second partitioning elements (14) define a plurality of cells (26); and arranging horizontal partitioning elements (24), through a pair of transverse slits (22) of a respective pair of successive first partitioning elements (12).

IPC Classes  ?

• F02C 7/045 - Air intakes for gas-turbine plants or jet-propulsion plants having provisions for noise suppression
• F02K 1/44 - Nozzles having means, e.g. a shield, reducing sound radiation in a specified direction
• F02K 1/82 - Jet pipe walls, e.g. liners
• B64C 1/40 - Sound or heat insulation

Abstract

A method for manufacturing a core (10) for a panel (100) for an aircraft comprises the steps of: arranging a plurality of first sheet- shaped partitioning elements (12), each having a plurality of vertical slits (16) extending transversely from a first edge thereof (12a), wherein the distance between two successive vertical slits (16) is not constant, spaced from each other; arranging a plurality of second sheet-shaped partitioning elements (14), each with a plurality of vertical slits (16), extending transversely from one of its first edges (14a), transversely on the first partitioning elements (12) so that each vertical slit (16) of the second partitioning elements (14) interlocks with a respective vertical slit (16) of a respective first partitioning element (12), to define a plurality of cells (26), each delimited laterally by a pair of opposing first partitioning elements (12) and a pair of opposing second partitioning elements (14).

IPC Classes  ?

• F02C 7/045 - Air intakes for gas-turbine plants or jet-propulsion plants having provisions for noise suppression
• F02K 1/44 - Nozzles having means, e.g. a shield, reducing sound radiation in a specified direction
• F02K 1/82 - Jet pipe walls, e.g. liners
• B64C 1/40 - Sound or heat insulation

Abstract

A convertible aircraft (1, 1') with an airframe (2) defining a first longitudinal axis (Y) is described; a pair of half-wings (3); a first, a second, a third, a fourth, a fifth and a sixth rotor (20a, 20b, 21a, 21b, 22a, 22b) rotatable about respective first, second, third, fourth, fifth and sixth axis (B, C, D, E, F, G), and operable independently of each other so as to generate respectively a first, a second, a third, a fourth, a fifth and a sixth thrust value (T1, T2, T3, T4, T5, T6) independent of each other; said fifth and sixth rotor (22a, 22b) being carried by respective said half-wings (3) and inclinable with respect to said airframe (2); the aircraft (1, 1') being switchable between a first hovering flight configuration wherein the sixth and seventh axis (F, G) are arranged orthogonal to the first axis (Y); and a second forward flight configuration wherein the sixth and seventh axis (F, G) are arranged parallel to or inclined with respect to the first axis (Y); the aircraft (1, 1') comprises first supports (32a, 32b) adapted to support the fifth and sixth rotor (22a, 22b) with respect to the respective half-wings (3); the first supports (32a, 32b) being arranged spaced apart from respective free ends (15) of respective half-wings (3) according to an extension direction of respective half-wings (3).

IPC Classes  ?

• B64C 27/28 - Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with forward-propulsion propellers pivotable to act as lifting rotors
• B64C 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft

Abstract

A series of convertible aircrafts (1, 1') with a core (100) with an airframe (2) defining a first axis (Y) is described; a first, a second, a third, a fourth, a fifth and a sixth rotor (20a, 20b, 21a, 21b, 22a, 22b) which are rotatable about respective first, second, third, fourth, fifth and sixth axis (B, C, D, E, F, G), and operable independently of each other so as to generate respectively a first, a second, a third, a fourth, a fifth and a sixth thrust value (T1, T2, T3, T4, T5, T6) independent of each other; the core (100) comprises an electric power source (81) and electric motors (72a, 72b, 73a, 73b, 74a, 74b) which are connected to said first, second, third, fourth, fifth and sixth rotor (20a, 20b, 21a, 21b, 22a, 22b); each aircraft (1, 1') of the series comprises a module (110, 120, 130, 140) associated with a respective architecture and interfaced with said core (100).

IPC Classes  ?

• B64C 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
• B64C 39/02 - Aircraft not otherwise provided for characterised by special use
• B64C 39/08 - Aircraft not otherwise provided for having multiple wings
• B64C 39/12 - Canard-type aircraft

Abstract

A series of convertible aircraft (1, 1') with a core (100) with an airframe (2) defining a first axis (Y) is described; a first, a second, a third, a fourth, a fifth and a sixth rotor (20a, 20b, 21a, 21b, 22a, 22b) which are rotatable about respective first, second, third, fourth, fifth and sixth axis (B, C, D, E, F, G), and operable independently of each other so as to generate respectively a first, a second, a third, a fourth, a fifth and a sixth thrust value (Tl, T2, T3, T4, T5, T6) independent of each other; the core (100) comprises first and second portions (11, 17) of respective half-wings (3) and aerodynamic surfaces (9) and each module (110, 120, 130, 140) comprises third and fourth portions (12, 18) of respective half-wings (3) and aerodynamic surfaces (9).

IPC Classes  ?

• B64C 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
• B64C 3/56 - Folding or collapsing to reduce overall dimensions of aircraft
• B64C 39/12 - Canard-type aircraft

Abstract

Method for recovering the digital error of a digital array antenna after powering it off/on again, the antenna (1) having a plurality of radiating elements (2), respective transmitting/receiving modules (3) operating at certain radio frequencies and a non- volatile memory (6), wherein at the end of a calibration of the antenna (1), for each radio frequency and each radiating element (2), a first and a second digital state (SCalRx, SCalTx) are acquired and recorded in the non-volatile memory (6) which are relative to the radio frequency in reception and, respectively, in transmission after powering the antenna (1) off and on again, for each radiating element (2), a third and a fourth digital state (SCurRx, SCurTx) are acquired which are relative to a certain test radio frequency in reception and, respectively, in transmission; for each radiating element (2), the third digital state (SCurRx) is compared with the first digital state (SCalRx) at the test radio frequency to determine first compensation coefficients (AtRx, AcpRx) and the fourth digital state (SCurTx) is compared with the second digital state (SCalTx) at the test radio frequency to determine second compensation coefficients (AtTx, ΔφΤx); the relative first compensation coefficients (AtRx, AφRx) in reception and the relative second compensation coefficients (ΔtΤx, ΔφΤx) in transmission are applied to each transmitting/receiving module (3).

IPC Classes  ?

• G01S 7/35 - RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES - Details of systems according to groups , , of systems according to group - Details of non-pulse systems
• G01S 7/40 - Means for monitoring or calibrating
• G01S 13/42 - Simultaneous measurement of distance and other coordinates
• G01S 13/02 - Systems using reflection of radio waves, e.g. primary radar systems; Analogous systems

Abstract

The installation comprises a traversing portion (12) configured to be rotatably mounted and supported on a stationary support structure, so as to rotate about a traversing axis (Z). There is an elevating portion (14) rotatably supported by the traversing portion (12) about an elevating axis (Y) perpendicular to the traversing axis (Z). A firearm assembly (16) supported by the elevating portion (14) comprises a barrel (18) configured to fire linkless ammunitions (A) through itself. A magazine (20) is configured to contain a plurality of linkless ammunitions (A) to be fed to the barrel (18). A feeding assembly (22) is configured to transfer the linkless ammunitions (A) from the magazine (20) to the barrel (18). The magazine (20) is carried by the traversing portion (12) and is operatively integral therewith. The feeding assembly (22) is carried by said elevating portion (14) and is operatively integral therewith. A transfer device (24) mounted on the traversing portion (12) is configured to transfer the linkless ammunitions (A) from the magazine (20) to the feeding assembly (22).

IPC Classes  ?

• F41A 9/02 - Feeding of unbelted ammunition using wheel conveyors, e.g. star-wheel-shaped conveyors
• F41A 9/04 - Feeding of unbelted ammunition using endless-chain belts carrying a plurality of ammunition
• F41A 27/00 - Gun mountings permitting traversing or elevating movement, e.g. gun carriages

Abstract

krfrii), as a function of the duration of the respective representative flight; and determining (250) a state of use of the group of aircraft, starting from the load sequence.

IPC Classes  ?

• G06Q 10/00 - Administration; Management
• G07C 5/00 - Registering or indicating the working of vehicles

Abstract

11wiiw1,11,181,18). The method includes detecting (800, 802,804, 806) anomalies of the transmission system (1) on the basis of the groups of synthetic indexes.

IPC Classes  ?

• B64D 45/00 - Aircraft indicators or protectors not otherwise provided for
• B64F 5/60 - Testing or inspecting aircraft components or systems
• B64C 27/12 - Rotor drives

Abstract

Device (1) for controlling a cursor (C) of a graphical user interface (2) of a flight unit (3), comprising a base structure (5); a graspable body (6) shaped to be grasped by a hand of an operator and movable with respect to the base structure (5) by the manual force provided by the operator by means of his/her hand; a force sensor (7) coupled to the graspable body (6) and designed to sense the movements of the graspable body (6) with respect to the base structure (5) along at least a first axis (X) and a second axis (Y); an interface circuit (8) for converting the signals provided by the force sensor (7) into control signal of the graphical user interface (2) of the flight unit (3) in order to move the cursor (C) along a first axis and a second axis of the graphical user interface (2) based on the force provided to the graspable body (6) by the operator.

IPC Classes  ?

• G05G 9/04 - Manually-actuated control mechanisms provided with one single controlling member co-operating with two or more controlled members, e.g. selectively, simultaneously the controlling member being movable in different independent ways, movement in each individual way actuating one controlled member only in which movement in two or more ways can occur simultaneously
• G06F 3/03 - Arrangements for converting the position or the displacement of a member into a coded form

Abstract

A test tool (1) for checking the profile of a structural component (2) is described, the tool (1) comprising a base (3) defining a support surface (4) for the structural component (2) and a plurality of force application devices (6) arranged in respective distinct positions along the base (3) at a predetermined distance from one another and each configured to apply, at the respective position, a control force to the structural component (2) supported by the base (3); wherein each force application device (6) comprises an actuation member (10) and a tip (11), and arrangeable, by means of the actuation member (10), between: an open position, in which the tip (11) is at a non-zero distance from the support surface (4) and from the structural component (2) resting on it, in use; and a closed position, in which the tip (11) is pressed against said structural component (2) to apply said control force thereon and thus push it completely against the support surface (4) to check the conformity of said profile to a specific tolerance; and wherein each force application device (6) further comprises: a spring member (14) operatively coupled to the tip (11) and compressible by means of said pressing of the tip (11) against the structural component (2); and an indicator element (15) carried by the spring member (14), having an external surface (16) with at least one distinctive surface feature (17) and movable by compression of the spring member (14) to render the distinctive surface feature (17) detectable or undetectable according to the extent of the control force applied, in use, to the structural component (2) by means of said pressing of the tip (11).

IPC Classes  ?

• G01L 1/04 - Measuring force or stress, in general by measuring elastic deformation of gauges, e.g. of springs
• B25B 5/12 - Arrangements for positively actuating jaws using toggle links
• F16B 31/02 - Screwed connections specially modified in view of tensile load; Break-bolts for indicating or limiting tensile load
• G01D 11/18 - Springs
• G01L 5/00 - Apparatus for, or methods of, measuring force, work, mechanical power, or torque, specially adapted for specific purposes
• G01M 5/00 - Investigating the elasticity of structures, e.g. deflection of bridges or aircraft wings

Abstract

An assembly for removably mounting an underwing pylon (11) to a rib (10) of an aircraft wing is described. The assembly comprises a prismatic body (12) insertable into a prismatic cavity (22) of the pylon, a threaded retaining element (14) having an upwardly tapered outer conical surface (15), and a vertical threaded pin (13) inserted through a vertical through hole (12e) of the prismatic body (12). The assembly further comprises an anti-rotation device (31, 32) for rotationally locking the threaded retaining element (14) to the prismatic body (12) relative to a vertical axis (A).

IPC Classes  ?

• B64D 7/04 - Arrangement of military equipment, e.g. armaments, armament accessories, or military shielding, in aircraft; Adaptations of armament mountings for aircraft the armaments being firearms fixedly mounted
• B64D 27/18 - Aircraft characterised by the type or position of power plant of jet type within, or attached to, wing

Abstract

A description is provided of a planetary gear (21; 21'') comprising a sun (15) rotatable around a first axis (B), a crown (17) angularly fixed with respect to the first axis (B); two satellites (19) that are meshing, rotatable around respective second axes (I); a satellite carrier (30) rotatable around the first axis (B) and comprising at least two first pins (32) with respect to which the satellites (19) are rotatable around respective second axes (I); and a plurality of bearings (40) comprising: a first ring (41) defining a first raceway (42) that is at least partially spherical; a second ring (43; 43'') defining a second raceway (44); and a plurality of rolling bodies (45; 46) shaped as an hourglass rolling on the first spherical raceway (42) and a second raceway (44); each rolling body (45; 46) being in contact with the raceways (42, 44) at a line (L1; L3, L2, L4) with axial ends (61; 63, 62; 64) lying on respective straight lines (R1; R3, R2; R4) tilted between them and converging in a point (S1; S2) lying on a median plane (P1; P2) of the rolling body (45; 46) and on the second axis (I); the straight lines (R1, R3; R2, R4) define a first angle (α1; α2), whose bisector (T1; T2) lies on the first median (P1; P2).

IPC Classes  ?

• B64C 27/12 - Rotor drives
• 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
• F16C 33/30 - Parts of ball or roller bearings
• F16C 33/36 - Rollers; Needles with grooves in the bearing surfaces
• F16C 33/46 - Cages for rollers or needles
• F16C 33/48 - Cages for rollers or needles for multiple rows of rollers or needles
• F16C 33/58 - Raceways; Race rings
• F16C 33/66 - Special parts or details in view of lubrication
• F16C 33/78 - Sealings of ball or roller bearings with a diaphragm, disc, or ring, with or without resilient members
• F16H 57/04 - Features relating to lubrication or cooling
• F16H 57/08 - General details of gearing of gearings with members having orbital motion

Abstract

The invention relates to a system (100) for sensing and recognizing acoustic anomalies and/or vibrational anomalies associated with a site to be monitored. The system comprises: - a unit (10) using optical fiber for the distributed acoustic sensing, DAS, and/or for the distributed vibrational sensing, DVS, of at least one acoustic and/or vibrational anomaly associated with the site and for generating an alarm signal (S1) representative of the sensing of such at least one anomaly; - one or more acoustic-electric transducers (20) operatively associated with the site to sense one or more ambient audio signals associated with the at least one acoustic and/or vibrational anomaly and to convert such ambient audio signals into electrical signals; - an audio classifier module (30) connected to such one or more acoustic-electric transducers and configured to classify the electrical signals generated based on at least one algorithm for data analysis and machine learning of information from the data, to generate a classification signal (S2) indicative of the fact that the at least one sensed anomaly is included in a set of recognized anomalies or is an unknown acoustic and/or vibrational anomaly; - a correlator module (40) configured to receive the alarm signal and the classification signal and to compare, during a sensing time interval (T1, T2, T3), such signals to generate a qualified alarm signal (S3); the qualified alarm signal is configured to provide coded information indicative of the fact that the alarm signal represents, in the sensing time interval, a recognized acoustic and/or vibrational anomaly or an unknown acoustic and/or vibrational anomaly.

IPC Classes  ?

• G01H 9/00 - Measuring mechanical vibrations or ultrasonic, sonic or infrasonic waves by using radiation-sensitive means, e.g. optical means

Abstract

nnn), and each being glued to both the support structure (12) and a respective n-th damping mass (14) in order to support said particular n-th damping mass on the support structure (12) so that the former is free to vibrate relative to the latter; wherein, for each n from 2 to N, each n-th damping mass (14) is arranged to at least partially surround an n-l-th damping mass (14); and wherein the first damping mass (14) has a solid semi-cylindrical shape, and the remaining damping masses (14) have a hollow semi-cylindrical shape.

IPC Classes  ?

• F16F 7/108 - Vibration-dampers; Shock-absorbers using inertia effect the inertia member being resiliently mounted on plastics springs
• B64C 1/40 - Sound or heat insulation

Abstract

An aircraft (1) capable of hovering is described, comprising a motor member (10); a rotor (5) connected to the motor member (10); a transmission shaft (11) rotatable around a first axis (B) and adapted to drive the rotor (5); and a transmission (9) interposed between the motor member (10) and the rotor (5) and comprising a planetary gear (21) formed by a sun (7) rotatable around a second axis (D); a crown (17) that is angularly fixed; and two satellites (19) meshing, each, with the crown (17) and the sun (15), and rotatable around respective third axes (I), which are, in turn, rotatable around the second axis (D); and a satellite carrier (30) rotatable around the second axis (D) and comprising two first pins (32) with respect to which the satellites (19) are rotatable around the respective third axes (E); the transmission (9) comprises an interface (50), angularly integral with the satellite carrier (30) around the second axis (D) and said transmission shaft (11) around the first axis (B); the interface (50) being coupled to said satellite carriers (30) and the transmission shaft (11) so as to allow an angular misalignment between the second axis (B) and a portion (55) of the interface (50).

IPC Classes  ?

• B64C 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
• B64D 35/00 - Transmitting power from power plant to propellers or rotors; Arrangements of transmissions
• B64C 27/12 - Rotor drives
• F02C 7/36 - Power transmission between the different shafts of the gas-turbine plant, or between the gas-turbine plant and the power user
• F16H 1/28 - Toothed gearings for conveying rotary motion with gears having orbital motion
• F16H 1/48 - Special means compensating for misalignment of axes
• F16H 57/08 - General details of gearing of gearings with members having orbital motion

Abstract

An anti-icing device (1) for intake opening (2) of the engine nacelle (3) comprising: a first Joule effect heater device (10) coupled to a first outer annular wall (5) of a front annular portion (4) of the nacelle and powered by electrical energy present on the aircraft; a second Joule effect heater device (11) coupled to a second inner annular wall (6) of the front annular portion (4), powered by electric energy present on the aircraft and configured, when powered, to heat the outer surface of the second inner wall (6) so that any ice formed on the second inner annular wall (6) is transformed into a film of water moving along the second annular wall (6) towards a sound-absorbing tubular wall (8); and a discontinuity element (12) provided between the second inner annular wall (6) and the sound-absorbing tubular wall (8) and configured to perform the detachment of the liquid film (F) flowing on the inner annular wall (6) due to the kinetic speed of the airflow sucked by the engine directing the nebulized water particles (G) towards the engine itself.

IPC Classes  ?

• B64D 15/00 - De-icing or preventing icing on exterior surfaces of aircraft
• B64D 15/12 - De-icing or preventing icing on exterior surfaces of aircraft by electric heating
• B64D 15/20 - Means for detecting icing or initiating de-icing
• B64D 15/22 - Automatic initiation by icing detector

Abstract

The system comprises a main structure (12) in which a firing chamber (14) and a braking and recovery tank (16), adjacent to the firing chamber (14), are positioned. The firing chamber (14) is intended for housing a firearm (18) configured for firing at least one projectile (P) into the braking and recovery tank (16). Furthermore, the braking tank (16) is configured for containing a liquid capable of braking the projectile (P) coming from the firing chamber (14) and fired by the firearm (18). Furthermore, the braking and recovery tank (16) has an opening (22) in front of which a barrel (20) of the firearm (18) is to be positioned. The opening (22) is configured to allow the projectile (P) to gain access to the braking and recovery tank (16) when the projectile (P) is fired by the firearm (18). There is also a counter barrel assembly (24) placed between the firing chamber (14) and the braking and recovery tank (16), and configured for receiving and guiding through itself the projectile (P) fired by the firearm (18), so as to cause the projectile (P) to enter the braking and recovery tank (16).

IPC Classes  ?

• F41J 13/00 - Bullet catchers

Abstract

The system (10) comprises a main structure (12) in which a firing chamber (14) and a braking and recovery tank (16), adjacent to the firing chamber (14), are positioned. The firing chamber (14) is intended for housing a firearm (18) configured for firing a projectile (P) into the braking and recovery tank (16). Furthermore, the braking and recovery tank (16) is configured for containing a liquid capable of braking the projectiles (P) coming from the firing chamber (14) and fired by the firearm (18). There is a collecting assembly (36) placed in the braking and recovery tank (16) and configured for recovering the braked projectiles (P) that have fallen to the bottom of the braking and recovery tank (16). The collecting assembly (36) comprises a basket (38) configured for receiving and collecting the fallen pro j ectiles (P), and a pushing device (42) configured for pushing the fallen projectiles (P) towards the basket (38).

IPC Classes  ?

• F41J 13/00 - Bullet catchers

Abstract

The system (10) comprises a main structure (12) in which a firing chamber (14) and a braking and recovery tank (16), adjacent to the firing chamber (14), are positioned. The firing chamber (14) is intended for housing a firearm (18) configured for firing a projectile (P) into the braking and recovery tank (16). Furthermore, the braking tank (16) is configured for containing a liquid capable of braking the projectile (P) coming from the firing chamber (14) and fired by the firearm (18). There is also a covering panel (48) configured for removably and reversibly closing the open top of the firing chamber (14).

IPC Classes  ?

• F41J 13/00 - Bullet catchers

Abstract

The invention relates to a monolithic structure (1) in composite material manufactured starting from a fiber-reinforced prepreg material and comprises two walls (6, 7) facing each other and at least one interconnection element (8) extending transversely between the walls (6, 7), connected to them and delimiting with the latter respective elongated cavities (9); wherein the walls (6, 7) extend symmetrically at opposite sides of a direction (B); the interconnection element (8) is a rib (10) extending transversely to the aforesaid direction (B); at least one wall (6, 7) has a sandwich configuration and comprises two panels (11, 12) facing each other and at least one spar member (13), which extends transversely between the panels (11, 12), is connected to them, delimits with the latter respective elongated cavities (14) and extends transversally to the rib (10).

IPC Classes  ?

• B29D 99/00 - Subject matter not provided for in other groups of this subclass
• B64C 3/20 - Integral or sandwich constructions
• B64C 5/02 - Tailplanes
• B29D 24/00 - Producing articles with hollow walls

Abstract

A method for the manufacture of a structural component (1) in composite material reinforced with stiffening stringers (2), defining, in use, at least part of an outer shell (3) of a vector (4) and comprising a skin (5) and a plurality of stringers (2) having a hollow section rigidly and integrally fixed to said skin (5), the method comprising the steps of: a) laminating a plurality of first layers (5a) of non cured or pre-cured composite material onto an external surface (6a) of a cure tool (6) to form said skin (5), so that a first face (5b) of said skin (5) defining, in use, the internal surface of the structural component (1) facing the internal environment of the vector (4) is facing the external surface (6a) of the tool (6); b) laminating respective pluralities of second layers (2a) of composite material on longitudinal hollow expandable inserts (10) to form a plurality of said stringers (2) each having a longitudinal axis (B), so that each stringer (2) is wound, at least partially, on an external surface (10a) of one respective hollow insert (10) so as to determine a longitudinal cavity (11) of each stringer (2) engaged by a relative hollow insert (10) and obtain in this way a plurality of reinforcing elements (12) each defined by one said stringer (2) wound on one said hollow insert (10); c) positioning each reinforcing element (12) on a second face (5c) of the skin (5) opposite to said first face (5b) and defining, in use, the external surface of the structural component (1) facing the environment external to the vector (4), and so that the cavities (11) of each stringer (2) face towards said second face (5c); d) holding each reinforcing element (12) on the second face (5c) of the skin (5) in a respective fixed position with respect to the tool (6); e) housing the tool (6), the skin (5) and the reinforcing elements (12) inside a vacuum bag (13); f) compacting together the first layers (5a) forming the skin (5) with the second layers (2a) forming the stringers (2) by applying the vacuum inside the vacuum bag (13); g) housing, after step f), tool (6), skin (5) and reinforcing elements (12) in a further vacuum bag (15); h) sealing the further vacuum bag (15) to delimit a vacuum chamber (16) therein; i) applying preset temperature and pressure to the outside of the vacuum chamber (16), in order to cure the composite material and determine the rigid and integral attachment of the stringers (2) to the second face (5c) of the skin (5). A structural component (1) obtained by the aforesaid manufacturing method is also described.

IPC Classes  ?

• B64C 1/06 - Frames; Stringers; Longerons
• B64F 5/10 - Manufacturing or assembling aircraft, e.g. jigs therefor
• B64G 1/22 - Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
• 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

Abstract

It is disclosed an indicator (16a) for an aircraft (1) capable of hovering, comprising a first indication (35) associated to the value of vertical speed of the aircraft (1) itself; the indicator (16a) comprises a first area (100) wherein a second indication (102) can be displayed that is associated to a Vortex Ring State condition being reached.

IPC Classes  ?

• B64C 27/00 - Rotorcraft; Rotors peculiar thereto
• B64C 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
• B64D 43/00 - Arrangements or adaptations of instruments
• B64D 45/00 - Aircraft indicators or protectors not otherwise provided for
• G01C 23/00 - Combined instruments indicating more than one navigational value, e.g. for aircraft; Combined measuring devices for measuring two or more variables of movement, e.g. distance, speed or acceleration

Abstract

pkpkpkkkkkkkkk) an output classifier (151;251;561;721) to generate estimates indicative of the probability that the aircraft (3) was performing manoeuvres belonging to the macrocategories (MC).

IPC Classes  ?

• G05B 23/02 - Electric testing or monitoring
• B64D 45/00 - Aircraft indicators or protectors not otherwise provided for

Abstract

A microphone calibration method, in particular a microphone for aeronautical use, comprising the following steps, coupling a reference microphone (3) to a first end (2-a) of a first standing-wave tube (2); coupling a microphone subjected to calibration (5) to a first end (4-a) of a second standing-wave tube (4); 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 (3, 5); 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 (3) and simultaneously detecting a first sound pressure value DB1t by means of the microphone subjected to calibration (5); further increasing the sound pressure of the acoustic input signal by a first amount ΔDΒ1 and detecting a second sound pressure value DB2r by means of the reference microphone (3) 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 -ΔDΒ2 greater than the first amount ΔDΒ1 and detecting a third sound pressure value DB3r by means of the reference microphone (3) and simultaneously detecting a third sound pressure value DB3t by means of the microphone subjected to calibration (5); again, increasing the sound pressure of the acoustic input signal by a third amount ΔDΒ3 and detecting a fourth sound pressure value by means of the reference microphone (3) and simultaneously detecting a fourth sound pressure value with the microphone subjected to calibration (5); 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.

IPC Classes  ?

• H04R 29/00 - Monitoring arrangements; Testing arrangements

Abstract

A method is described for manufacturing a structural element (2) in composite material extending along a straight or curvilinear longitudinal direction (D), having a Z-shaped cross section and comprising, in its final configuration, a central web (2a) and two flanges (2b, 2c) extending at a given final angle from opposite end portions of the web (2a) in respective directions opposite to one another; the method including the steps of: arranging a plurality of layers (3) of composite material on a shaped portion (4) of a forming mold; laminating the layers (3) on the shaped portion (4) so that the web (2a) is arranged, at least partially, in its final configuration, that a first flange (2b) is arranged in its final configuration at the final angle with respect to the portion of the web (2a) arranged in its final configuration, and that a second flange (2c) 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 (2a) arranged in its final configuration; moving a movable portion (6) of the forming mold, which is movable with respect to a fixed portion (5) of the forming mold, from a rest position to a bending position; displacing the second flange (2c) from the initial configuration into a final configuration in which it is at said final angle with respect to the portion of the web (2a) arranged in its final configuration; the step d) of displacing being carried out by means of the step c) of moving.

IPC Classes  ?

• B29C 70/38 - Automated lay-up, e.g. using robots, laying filaments according to predetermined patterns
• B29D 99/00 - Subject matter not provided for in other groups of this subclass
• B29B 11/16 - Making preforms characterised by structure or composition comprising fillers or reinforcements
• B29C 53/04 - Bending or folding of plates or sheets
• B64C 1/06 - Frames; Stringers; Longerons
• B64C 3/18 - Spars; Ribs; Stringers
• 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 70/44 - 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
• B64C 1/00 - Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like

Abstract

The system (10) and the method envisage the use of a carrier (12) intended to house an assembly (14) to be subjected to a shock test. The carrier (12) is a container or casing which is reclosable after having inserted the assembly (14) therein. There is a tubular guide (16) having a pair of ends (18, 20) and defining an inner cavity (22) through which the carrier (12) is movable, in a guided manner, between such ends (18, 20). A thrust tank (24) contains a pressurized fluid and is connected to the inner cavity (22) in proximity to one end (18) of the tubular guide (16) and in a position upstream of the carrier (12). The pressurized fluid can thrust the carrier (12) through the inner cavity (22) towards the other end (20) of the tubular guide (16), subjecting the carrier (12) to a thrust acceleration suitable for simulating the effects of a shock undergone by the assembly (14).

IPC Classes  ?

• G01M 7/08 - Shock-testing

Abstract

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 (25) having at least one right triangle shaped portion, and the spars carried by the respective rectilinear supports (25) are subsequently arranged on a stratified structure (4) carried by a mould (1). A vacuum bag (42) is created which covers the stratified structure (4), the rectilinear supports (25), and the J shaped spars. Holes (F) are created in the vacuum bag at respective connection points (50) made along each rectilinear support (25). A supporting structure (30) provided with hooking and adjusting elements (31) with the connection points (50) adjusts the position of each hooking and adjusting element (31) with respect to the supporting structure (30) in order to position the rectilinear support (25) in a direction parallel to the vertical so that the position of the end portion (12) of the J shaped spar, with respect to the mould, corresponds to that foreseen by the design.

IPC Classes  ?

• B29C 65/00 - Joining of preformed parts; Apparatus therefor
• 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 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
• B29L 31/30 - Vehicles, e.g. ships or aircraft, or body parts thereof
• B29K 105/24 - Condition, form or state of moulded material cross-linked or vulcanised

Abstract

NN/2NN/2NN/2N/2NN respective transmission and/or reception front-end modules (59, 6) and configured to carry out beam steering functions including signal phase-shifting, and attenuation and/or amplification functions.

IPC Classes  ?

• 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
• H01Q 3/26 - 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
• H01Q 1/02 - Arrangements for de-icing; Arrangements for drying-out
• H01Q 21/00 - Antenna arrays or systems

Abstract

The method for manufacturing a panel (10) for aircraft comprises the steps of: arranging, on a curing surface (22), a skin (12) of pre-preg composite material; arranging a plurality of pre-formed, uncured composite stringers (14), each having an open cross section with a web (16) and a base (18) transverse to each other so that a first base portion (18a) protrudes toward a first side (SX) and a second base portion (18b) protrudes toward a second side (DX); arranging said plurality of stringers (14) on the skin (12) with the base (18) in contact with the skin (12); arranging, on each stringer (14), a respective first mandrel (M1) so as to completely cover said first base portion (18a) and a respective second mandrel (M2) so as to completely cover said second base portion (18b); and having the skin (12) and the plurality of stringers (14) undergo a co-curing process in autoclave with vacuum bag.

IPC Classes  ?

• B64C 3/24 - Moulded or cast structures
• 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

Abstract

The present invention relates to a product comprising a substrate (9) and a multilayer coating (1) for the thermal control of a surface (6) comprising a first inner layer (2) intended to be deposited on said surface, a second intermediate layer (3) applied on said first inner layer (2) and a third outer layer (4) applied on said second intermediate layer (3) in which: said first inner layer (2) comprises a co-dispersion of conductive nanoparticles and dielectric nanoparticles, wherein the volume fraction of conductive nanoparticles increases along the thickness of said first inner layer moving away from said second intermediate layer (3); said second intermediate layer comprises a plurality of layers wherein at least one layer of a dielectric material transparent in the visible with a high refractive index in the visible (3') is alternated with at least one layer of a dielectric material transparent in the visible with a low7 refractive index in the visible (3') and wherein the refractive index of each layer of dielectric material transparent in the visible with high refractive index in the visible (3') is higher than the refractive index of each adjacent layer of dielectric material transparent in the visible with low refractive index in the visible (3') and said third outer layer (4) made of a conductive oxide transparent in the visible having a resistivity of less than 1x10-3 ohm x cm. There is also provided an optical solar reflector comprising the product.

IPC Classes  ?

• G02B 1/16 - Optical coatings produced by application to, or surface treatment of, optical elements having an anti-static effect, e.g. electrically conducting coatings
• G02B 5/08 - Mirrors
• G02B 5/28 - Interference filters
• B82Y 20/00 - Nanooptics, e.g. quantum optics or photonic crystals
• H01L 31/054 - Optical elements directly associated or integrated with the PV cell, e.g. light-reflecting means or light-concentrating means
• F24S 23/70 - Arrangements for concentrating solar rays for solar heat collectors with reflectors

Abstract

An isostatic mounting system (1) is described to support a sensor (2) and to minimise the thermal conductivity between the sensor (2) and a carrier thereof. An isostatic mounting system (1) comprises at least one support foot (6) configured to be fixed, in use, to a structure (4) of the carrier, and at least one leg (7) extending from the support foot (6). The support foot (6) is.made of a full solid material and the leg (7) has a lattice structure (11) made of the same material of the support foot (6).

IPC Classes  ?

• F16M 11/22 - Undercarriages with or without wheels with approximately constant height, e.g. with constant length of column or of legs
• 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
• B22F 10/00 - Additive manufacturing of workpieces or articles from metallic powder

Abstract

A method for controlling an aircraft (1) capable of hovering is described, comprising a first engine (10a); a second engine (10b); at least one rotor (3); and a transmission (8) interposed between the first and second engine (10a, 10b) and the rotor (3); the transmission (8) comprises a first and a second inlet (12a, 12b) connected respectively to a first outlet member (11a) of the first engine (10a) and to a second outlet member (11b) of the second engine (10b); the method comprises step i) of placing the aircraft (1) in a first configuration, in which the first and second engine (10a, 10b) make available a first and a second power value (PI, P2); or in a second configuration, in which the first engine (10a) makes available a third power value (P3) greater than the first power value (P1) to the first inlet (12a), and the second engine (10b) delivers a nil power value (P4) to the second inlet (12b); 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 (1); and iii) enabling the transition of the aircraft (1) from the first configuration to the second configuration, when the parameters assume respective first values.

IPC Classes  ?

• F02C 7/36 - Power transmission between the different shafts of the gas-turbine plant, or between the gas-turbine plant and the power user
• F02C 3/113 - Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor with two or more rotors connected by power transmission with variable power transmission between rotors
• F02C 6/02 - Plural gas-turbine plants having a common power output

Abstract

Process for manufacturing a structural component (1, 1', 1", 1"', 1"") made of composite material comprising a skin (2) and at least one stiffening stringer (3, 3', 3", 3"', 3"") applied rigidly and integrally to one face (2a) of the skin (2); the process comprises the following steps: • a) arranging on a tool (12, 12', 12", 12"") a plurality of first layers (4; 4a', 4b'; 4"; 4'" 4a"", 4b"", 4c"") of uncured or precured composite material forming the stringer (3, 3', 3", 3", 3"") presenting a longitudinal axis (A) and having a raised portion (7, 7', 7", 7'", 7"") protruding from at least one flange (8) extending parallel to the longitudinal axis (A) and along a lying surface that is flat or is a surface of revolution (S);) b) arranging on said tool (12, 12', 12", 12'", 12"") a plurality of second layers of uncured or pre-cured composite material forming said skin (2); c) making a face (2a) of said skin (2), parallel to said lying surface (S), and said flange (8) of said stringer (3, 3', 3", 3'", 3"") adhere to each other; d) applying predetermined temperature and pressure on the assembly thus formed so as to compact said layers together, possibly curing the uncured material and rigidly joining said skin (2) to said stringer (3, 3', 3". 3'", 3""); and e) performing a cutting operation on the free end side edge/s (13) of said flange (8) in a slanted direction with respect to said lying surface/s and in such a way that the cut layers (4, 4a', 4b', 4", 4'", 4a"", 4b"") of said flange (8) have, in the subsequent phase c), an extension along said lying surface/s, increasing towards the skin (2) itself.

IPC Classes  ?

• B64C 1/06 - Frames; Stringers; Longerons
• B64C 3/18 - Spars; Ribs; Stringers
• B64C 3/24 - Moulded or cast structures
• 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
• B29C 70/64 - Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising fillers only the filler influencing the surface characteristics of the material, e.g. by concentrating near the surface or by incorporation into the surface by force
• B29D 99/00 - Subject matter not provided for in other groups of this subclass
• B32B 5/26 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by the presence of two or more layers which comprise fibres, filaments, granules, or powder, or are foamed or specifically porous one layer being a fibrous or filamentary layer another layer also being fibrous or filamentary
• B32B 5/14 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by a layer differing constitutionally or physically in different parts, e.g. denser near its faces
• B32B 13/14 - Layered products essentially comprising a water-setting substance, e.g. concrete, plaster, asbestos cement, or like builders' material next to a fibrous or filamentary layer
• B32B 33/00 - Layered products characterised by particular properties or particular surface features, e.g. particular surface coatings; Layered products designed for particular purposes not covered by another single class
• B32B 38/00 - Ancillary operations in connection with laminating processes
• B64C 1/00 - Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like

Abstract

Process for manufacturing a structural component (1, 1', 1", 1''', 1"" ) made of composite material comprising a skin (2) and at least one stiffening stringer (3, 3', 3", 3"', 3"") applied rigidly and integrally to one face (2a) of the skin (2); the process comprises the following steps: a) arranging on a tool (12, 12', 12", 12''', 12"") a plurality of first layers (4; 4a', 4b'; 4"; 4'"'; 4a"", 4b"", 4c"") of uncured or p re-cured composite material forming the stringer (3, 3', 3", 3'", 3"") presenting a longitudinal axis (A) and having a raised portion (7, 7', 7", 7''', 7"" ) protruding from at least one flange (8) extending parallel to the longitudinal axis (A) and along a lying surface that is flat or is a surface of revolution (S);) b) arranging on said tool (12, 12', 12", 12''', 12"") a plurality of second layers of uncured or p re-cured composite material forming said skin (2); c) making a face (2a) of said skin (2), parallel to said lying surface (S), and said flange (8) of said stringer (3, 3', 3", 3'", 3"") adhere to each other; d) applying predetermined temperature and pressure on the assembly thus formed so as to compact said layers together, possibly curing the uncured material and rigidly joining said skin (2) to said stringer (3, 3', 3", 3'", 3"" ); and e) performing a cutting operation on the free end side edge/s (13) of said flange (8) in a transversal direction with respect to said lying surface (S); and f) cover said end side edge/s (13) of the end of said flange (8) with a coating of composite material so as to seal outwards the layers (4; 4a', 4b'; 4 "; 4'"; 4a"", 4b"") forming said flange (8).

IPC Classes  ?

• B64C 1/06 - Frames; Stringers; Longerons
• B64C 3/18 - Spars; Ribs; Stringers
• B64C 3/24 - Moulded or cast structures
• 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
• B29C 70/64 - Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising fillers only the filler influencing the surface characteristics of the material, e.g. by concentrating near the surface or by incorporation into the surface by force
• B29D 99/00 - Subject matter not provided for in other groups of this subclass
• B32B 5/26 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by the presence of two or more layers which comprise fibres, filaments, granules, or powder, or are foamed or specifically porous one layer being a fibrous or filamentary layer another layer also being fibrous or filamentary
• B32B 5/14 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by a layer differing constitutionally or physically in different parts, e.g. denser near its faces
• B32B 13/14 - Layered products essentially comprising a water-setting substance, e.g. concrete, plaster, asbestos cement, or like builders' material next to a fibrous or filamentary layer
• B32B 33/00 - Layered products characterised by particular properties or particular surface features, e.g. particular surface coatings; Layered products designed for particular purposes not covered by another single class
• B32B 38/00 - Ancillary operations in connection with laminating processes

Abstract

The invention relates to an auxiliary device (10) for guiding a portable rotary drill (A) and for the suction of dust and scraps generated by drilling or countersinking operations performed by the drill (A); the auxiliary device (10) comprises: a first and a second operating unit (11, 12), which are configured to be arranged on opposite sides of an element (D) or of a plurality of elements (C, D) to be drilled stacked at least partially with each other and define respectively a first and a second through channel (13, 16) available in use coaxially with each other to be engaged by a drill bit (P) of the drill (A); adjustable distance constraint means (40) connecting the first and second operating units (11, 12) and selectively operable to adjust the distance between the first and second operating units (11, 12) to a value correlated with or corresponding to the thickness of the at least partially stacked element (D) or elements (C, D) to be drilled; and a channeling system (41) connecting the first and second channels (13, 16) with a suction source to allow in use the suction of dust and scraps generated by the drill (A).

IPC Classes  ?

• B23Q 11/00 - Accessories fitted to machine tools for keeping tools or parts of the machine in good working condition or for cooling work; Safety devices specially combined with or arranged in, or specially adapted for use in connection with, machine tools
• B23Q 9/00 - Arrangements for supporting or guiding portable metal-working machines or apparatus
• B08B 15/04 - Preventing escape of dirt or fumes from the area where they are produced; Collecting or removing dirt or fumes from that area from a small area, e.g. a tool
• B23B 47/34 - Arrangements for removing chips out of the holes made; Chip-breaking arrangements attached to the tool
• B23B 47/28 - Drill jigs for workpieces

Abstract

A rotor (8, 8', 106''', 106'''', 106''''', 106'''''') for an aircraft (1, 100) is described, comprising an input shaft (10, 108) rotatable around a first axis (C, I); an output member (15, 112) rotatable around a second axis (D, J); a coupling element (20, 20', 20'', 20''') functionally interposed between the input shaft (10, 108) and the output member (15, 112) and adapted to transmit the motion from the input shaft (10, 108) to the output member (15, 112); the coupling element (20, 20', 20'', 20''') is configured to allow, in use, a fixed or variable inclination between the respective first and second axes (C, I, D, J); the coupling element (20, 20', 20'', 20''') comprises at least a first corrugated element (21, 22, 25, 120''', 121''', 120'''', 121'''', 122'''') made of an elastically deformable material; the first corrugated element (21, 22, 25; 120''', 121'''; 120'''', 121'''', 122'''') allows the inclination through elastic deformation.

IPC Classes  ?

• B64C 27/12 - Rotor drives
• F16D 3/70 - 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 comprising elastic elements arranged in holes in one coupling part and surrounding pins on the other coupling part
• F16D 21/02 - Systems comprising a plurality of mechanically-actuated clutches for interconnecting three or more shafts or other transmission members in different ways
• F16D 3/62 - 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 comprising pushing or pulling links attached to both parts the links or their attachments being elastic
• 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
• F16D 3/74 - 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 the intermediate member or members being made of rubber or other flexible material
• F16D 3/50 - 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
• B64C 27/22 - Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft

Abstract

A helicopter (1) is described comprising a motor member (3) comprising an output shaft (12) and a first stator (11, 29) rotatably supporting the output shaft (12) around a first axis (C); a main rotor (4) adapted to provide the lift necessary for the support and the thrust necessary for the movement of the helicopter (1); a transmission (7) interposed between the motor member (3) and the main rotor (4); the transmission (7) comprises, in turn, an input shaft (21) rotatable around a second axis (D) and a second stator (20, 30) rotatably supporting the input shaft (21) around the second axis (D); the helicopter (1) also comprises a joint (35) interposed between the first and second stator (11, 29; 20, 30), angularly fixed with respect to the first axis (C), and configured to allow an inclination between the first and second stator (11, 29; 20, 30) in a plane parallel to said first axis (C); the joint (35) comprises a first corrugated element (36) made of an elastically deformable material, interposed between said first and second stator (11, 29; 20, 30), and adapted to allow the inclination through elastic deformation.

IPC Classes  ?

• B64C 27/12 - Rotor drives
• 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 27/14 - Direct drive between power plant and rotor hub
• 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
• F16D 3/74 - 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 the intermediate member or members being made of rubber or other flexible material

Abstract

The thrust reverser system (60) for an aircraft turbofan propulsion system (30) comprises: a fixed structure (80) and a translating structure (90) adapted to define between them a sequential flow path for air, the translating structure (90) being slidable along an axial direction (10) between a stowed position, wherein it is connected with said fixed structure (80), and an opening position, wherein it is spaced apart from said fixed structure (80) in an axial direction (10) so as to define a circumferential opening (12) for the outflow of air to the external environment; and an iris mechanism (190) having a plurality of blades (140) that are jointly movable between a rest configuration, wherein they jointly define a passage for air, and a deployed configuration wherein they at least partially occlude a bypass duct (430) of the turbofan propulsion system (30).

IPC Classes  ?

• 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
• F02K 1/60 - Reversing jet main flow by blocking the rearward discharge by means of pivoted eyelids or clamshells, e.g. target-type reversers

Abstract

There is described an aircraft (1) configured to be able to hover, comprising a fuselage (2); and a support element (13, 55) adapted to support a load (10, 51), made of elastically deformable material and constrained to said fuselage (2); the support element (13, 55) being movable in an operating position in which it is arranged at least partially outside said fuselage (2) and supports said load (10, 51); the aircraft (1) comprises a sock (20, 60) surrounding the support element (13, 55) arranged in said operating position; the sock (20, 60) is configured to contain the elastic return of the support element (13, 55), in case the support element (13, 55) arranged in said operating position is sheared off.

IPC Classes  ?

• B64D 1/22 - Taking-up articles from earth's surface
• B64C 27/04 - Helicopters
• B64D 1/02 - Dropping, ejecting, or releasing articles
• B64D 1/08 - Dropping, ejecting, or releasing articles the articles being load-carrying devices
• B66C 1/12 - Slings comprising chains, wires, ropes, or bands; Nets

Abstract

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).

IPC Classes  ?

• B33Y 50/02 - Data acquisition or data processing for additive manufacturing for controlling or regulating additive manufacturing processes
• B33Y 10/00 - Processes of additive manufacturing
• 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]
• B29C 64/393 - Data acquisition or data processing for additive manufacturing for controlling or regulating additive manufacturing processes
• B29C 70/38 - Automated lay-up, e.g. using robots, laying filaments according to predetermined patterns
• G06F 30/20 - Design optimisation, verification or simulation
• B64C 1/00 - Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
• B64C 3/20 - Integral or sandwich constructions

Abstract

An aircraft (1) with a motor bay (8) is described; a motor system (6) with a discharge duct (17); a heat exchanger (20) arranged outside said motor system (6); a first air intake (25); a first duct (26) along which the heat exchanger (20) is arranged; a first converging nozzle (15) having a downstream section (39) fluidically connected with the discharge duct (17) and with the first duct (26) so as to create a first flow rate of air adapted to cool the heat exchanger (20); and a second air intake (10) that is open in the motor bay (8) and distinct from the first air intake (25); a second converging nozzle (16) having a second downstream section (49) fluidically connected with the discharge duct (17) and with the motor bay (8), so as to create a second flow rate of cooling air of the motor bay (8) directed from the second air intake (10) towards the discharge duct (17) and by-passing the motor system (6).

IPC Classes  ?

• B64D 33/08 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
• B64D 33/10 - Radiator arrangement
• B64C 27/04 - Helicopters

Abstract

A helicopter (1) is described comprising a fuselage (2) elongated along a first axis (X) and extending between a nose (6) and a tail boom (7); a tailplane (9) with a pair of first aerodynamic surfaces (11) elongated along a second axis (Y); the first and second axis (X, Y) define a first plane (Q); the helicopter (1) comprises a pair of elements (20) transversal to the first aerodynamic surfaces (11); and a pair of second aerodynamic surfaces (21) generating respective second aerodynamic forces, connected to first elements (20), and facing and spaced from respective first aerodynamic surfaces (11); each second aerodynamic surface (21) comprises one first root end (80) connected to the respective said element (20), a second free end (81) spaced from said tail boom (7), a first leading edge (55), a first trailing edge (56) opposite to said first leading edge (55), a first chord (C1) at said first root end (80) and a second chord (C2) at said second free end (81) parallel to said first axis (X); the first and the second chord (C1, C2) define a second plane (R) tilted with respect to said first plane (Q).

IPC Classes  ?

• B64C 5/02 - Tailplanes
• B64C 27/04 - Helicopters
• 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 39/06 - Aircraft not otherwise provided for having disc- or ring-shaped wings
• B64C 3/14 - Aerofoil profile

Abstract

The multifunctional composite material comprises a polymeric matrix filled with electrically conductive nanoparticles combined with a self-healing molecular filler selected in the group consisting of molecules and oligomers containing groups acting as donors and acceptors of hydrogen bonds.

IPC Classes  ?

• C08L 63/00 - Compositions of epoxy resins; Compositions of derivatives of epoxy resins
• H01B 1/24 - Conductive material dispersed in non-conductive organic material the conductive material comprising carbon-silicon compounds, carbon, or silicon

Abstract

A fixed-wing aircraft (1) provided with a fuselage (3) which extends along a longitudinal axis (L), a pair of wings, a propulsion system and a vertical stabilizer (5) provided with a vertical drift (6) fixed with respect to the fuselage (3), The drift (6) has a through seat (8) which houses at least one thrust generator (12) adapted to produce in a controllable manner an air flow (F) along a transverse axis (T) from a first side of the drift (6) or from a second side of the drift opposite the first one, producing aerodynamic forces which act on the opposite faces (6a, 6b) of the drift (6) and are used for the directional control of the aircraft (1).

IPC Classes  ?

• B64C 5/06 - Fins
• B64C 11/00 - Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
• B64C 15/14 - Attitude, flight direction or altitude control by jet reaction the jets being other than main propulsion jets

Abstract

ex,indindsssrotex,indrotrsssssss") induced in the stator winding (7).

IPC Classes  ?

• H02P 6/32 - Arrangements for controlling wound field motors, e.g. motors with exciter coils
• H02P 9/30 - Arrangements for controlling electric generators for the purpose of obtaining a desired output by variation of field using discharge tubes or semiconductor devices using semiconductor devices

Abstract

A cargo door (10) for an aircraft comprises a series of locking devices (13) spaced near an edge of the cargo door, a vent panel (11), a control handle (16), and a torsion shaft (14), which actuates a series of pins (19) to lock and unlock the locking devices (13). A first drive (18) connects the control handle (16) to the torsion shaft (14) to rotate the torsion shaft (14) following a locking or unlocking command imparted to the control handle (16). A second drive (20) connects the torsion shaft (14) to the vent panel (11) to open or close the vent panel (11) following a rotation of the torsion shaft (14). The torsion shaft (14) is a double shaft comprising two coaxial and rotationally integral shafts, with an inner shaft (21) and an outer tubular shaft (22).

IPC Classes  ?

• B64C 1/14 - Windows; Doors; Hatch covers or access panels; Surrounding frame structures; Canopies; Windscreens
• E05C 9/00 - Arrangement of simultaneously-actuated bolts or other securing devices at well-separated positions on the same wing

Abstract

A rotor (3, 4) for an aircraft (1) is described having: a support (9) angularly fixed with respect to an axis (B, C) and housing a power source (20); a unit (11, 12) rotatable about axis (B, C) and housing an electrical load (21, 24) of the resistive type; and a power supply system (19, 19', 19'', 19''', 19'''', 19''''', 19'''''', 19''''''') for the electrical load (21, 24) and comprising: a first transformer (22) electrically interposed between the power source (20) and the load (21, 24); the first transformer (22) comprises: a first winding (26) arranged on the support (9) and a second winding (28) arranged on the unit (11, 12, 13), a stator (9) carried by the support (9), rotationally fixed with respect to axis (B, C) and to which the first winding (26) is fixed; and a rotor (101) operatively connected to the unit (11, 12) and to which the second winding (28) is fixed; the power supply system (19, 19', 19'', 19''', 19'''', 19''''', 19'''''', 19''''''') comprises a capacitive circuit (50) electrically connected to the first transformer (22), so as to reduce the reactive power absorbed by the rotary transformer (22).

IPC Classes  ?

• B64D 15/12 - De-icing or preventing icing on exterior surfaces of aircraft by electric heating
• B64C 27/06 - Helicopters with single rotor
• H05B 1/02 - Automatic switching arrangements specially adapted to heating apparatus
• H01F 38/18 - Rotary transformers

Abstract

A helicopter (1) is described comprising: a tail boom (7); a fin (8) projecting from the tail boom (7); and a tailplane (9) arranged at the tail boom (7) and transversal to the fin (8); at least one of the fin (8) and the tailplane (9) defining a first aerodynamic surface (10, 11) generating a first aerodynamic force; at least one first element (20, 90) transversal to the first aerodynamic surface (10, 11); and a second aerodynamic surface (21, 92) generating a second aerodynamic force, connected to the first element (20, 90), facing and spaced from the first aerodynamic surface (10, 11); the second aerodynamic surface (21, 92) is spaced from the other of the fin (8) and the tailplane (9).

IPC Classes  ?

• B64C 5/02 - Tailplanes
• B64C 5/06 - Fins
• 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 3/16 - Frontal aspect

Abstract

An aircraft (1) is described comprising a transmission unit (9) with a first module (11, 13, 15) and a lubrication system (25, 25'); the first module (11, 13, 15) comprises a casing (20) and a movable member (17, 18, 19); the lubrication system (25, 25') comprises a header (26), a nozzle (27, 28) fed with the lubricating fluid and designed to feed the lubricating fluid inside the casing (20) of the first module (11, 13, 15), a collection tank (30, 100') for the lubricating fluid injected by the nozzle (27, 28), and recirculation means (35) designed to cause the recirculation of the lubricating fluid from the collection tank (30, 100') to the feed header (26); the first module (11, 13, 15) comprises a valve (60, 60') available in a first configuration, in which it enables the outflow of said lubricating fluid from said module (11) to the recirculation means (35) when the pressure of the lubricating fluid inside the header (26) is greater than a threshold value; and in a second configuration, in which it fluidically isolates the module (11) from the recirculation means (35) when the pressure of the lubricating fluid inside the header (26) is less than the threshold value.

IPC Classes  ?

• B64C 27/14 - Direct drive between power plant and rotor hub
• B64C 27/00 - Rotorcraft; Rotors peculiar thereto
• B64D 35/00 - Transmitting power from power plant to propellers or rotors; Arrangements of transmissions
• 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

Abstract

A convertiplane (1, 1', 1'') is described that comprises: a fuselage (2), having a first longitudinal axis (A) and, in turn, comprising a nose (12) and a tail portion (13); a pair of wings (3) arranged on respective opposite sides of the fuselage (2), carrying respective rotors (5) and generating a lift value; and a pair of engines (4) operatively connected to respective rotors (5); each rotor (5) comprising a mast (9) rotatable about a second axis (B) between a helicopter configuration and an aeroplane configuration; each rotor (4) is interposed between the fuselage (2) and the relative rotor (5) along the direction of extension of the relative wing (3).

IPC Classes  ?

• B64C 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
• B64D 27/14 - Aircraft characterised by the type or position of power plant of gas-turbine type within, or attached to, fuselage
• B64C 39/12 - Canard-type aircraft
• B64D 27/24 - Aircraft characterised by the type or position of power plant using steam, electricity, or spring force
• B64C 3/56 - Folding or collapsing to reduce overall dimensions of aircraft
• B64D 27/12 - Aircraft characterised by the type or position of power plant of gas-turbine type within, or attached to, wing
• B64C 1/14 - Windows; Doors; Hatch covers or access panels; Surrounding frame structures; Canopies; Windscreens
• B64D 1/06 - Bomb releasing; Bomb doors
• B64D 47/08 - Arrangements of cameras
• B64D 7/06 - Arrangement of military equipment, e.g. armaments, armament accessories, or military shielding, in aircraft; Adaptations of armament mountings for aircraft the armaments being firearms movably mounted
• B64D 27/02 - Aircraft characterised by the type or position of power plant

Abstract

A Multi-Beam on Receive Electronically Steerable Antenna (1) comprising a Tx array (2, 6) comprising a phased array of Tx antenna elements (3, 7) and having a geometric aperture with one or more pairs of parallel opposite sides; and an Rx array (2, 4) comprising a phased array of Rx antenna elements (3, 5) 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 (2, 6) are inclined relative to one or more pairs of parallel opposite sides of the geometric aperture of the Rx array (2, 4).

IPC Classes  ?

• H01Q 21/06 - Arrays of individually energised antenna units similarly polarised and spaced apart
• H01Q 21/28 - Combinations of substantially independent non-interacting antenna units or systems
• H01Q 25/00 - Antennas or antenna systems providing at least two radiating patterns
• G01S 7/28 - RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES - Details of systems according to groups , , of systems according to group - Details of pulse systems
• H01Q 21/22 - Antenna units of the array energised non-uniformly in amplitude or phase, e.g. tapered array or binomial array
• H01Q 3/26 - 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

Abstract

A convertiplane (1, 1', 1 '') is described that comprises a fuselage (2), having a first longitudinal axis (A), with a nose (12) and a tail portion (13); a pair of wings (3) arranged on respective opposite sides of said fuselage (2), carrying respective rotors (5); a pair of engines (4) operatively connected to respective said rotors (5); at least one first lifting surface (19, 16) arranged on said tail portion (13); and a pair of canards (14) arranged on said nose (12) of said fuselage (2) and defining respective second lifting surfaces adapted to generate a third lift/negative lift value; each rotor (5) comprising a mast (9) rotatable about a second axis (B) and about an relative third axis (E) transversal to said second axis (B) and with respect to the fuselage (2), so as to set said convertiplane (1, 1', 1'') between a helicopter configuration and an aeroplane configuration; each second axis (B), in use, being transversal to the first axis (A) of said convertiplane (1, 1', 1'') in said helicopter configuration and being parallel to said first axis (A) in said aeroplane configuration.

IPC Classes  ?

• 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 39/12 - Canard-type aircraft

Abstract

A method is described for the folding of a convertiplane (1) with a fuselage (2) having a first axis (A), a pair of wings (3) and a pair of rotors (5) arranged on respective mutually opposite sides of the respective wings (3); each rotor (5) comprises a mast (9) rotatable about a second axis (B) and a plurality of blades (8a, 8b); each wing (3) comprises a first portion (20) fixed with respect to the fuselage (2); a second tip portion (21) opposite to the first portion (20); and a third intermediate portion (22), which is interposed between the associated first portion (20) and second tip portion (21); the mast (9) of each rotor (5) is integrally tiltable with the second axis (B) and associated second tip portion (21) about a third axis (E) transversal to the second axis (B) and the fuselage (2) so as to set said convertiplane (1) between a helicopter configuration and an aeroplane configuration; the method comprises the steps i) of arranging the convertiplane (1) in the helicopter configuration and ii) rotating a pair of assemblies (23) of respective wings (3) with respect to the fuselage (2) and the associated first portion (20) about respective fifth axes (I), so as to arrange the convertiplane (1) in a stowage configuration. A convertiplane (1) is also disclosed.

IPC Classes  ?

• 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 3/56 - Folding or collapsing to reduce overall dimensions of aircraft
• B64C 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft

Abstract

A system for measuring a deformation of a structure arranged to be installed on an aircraft is described, comprising: - deformation sensor means which are arranged to be associated with the structure and to assume an electrical resistance value indicative of the deformation of this structure and which include two electrical connection terminals which are short-circuited so as to recreate a closed circuit; - magnetic field excitation means which are arranged to generate a magnetic field concatenated with the closed circuit, so as to generate an induced current, and which include a laser generator; - electromagnetic radiation transmission means included in the closed circuit, arranged to emit an electromagnetic radiation of which the value is a function of the electrical resistance of the deformation sensor means, and including an antenna; - electromagnetic radiation receiving means including an antenna and arranged to receive the electromagnetic radiation transmitted by the electromagnetic radiation transmission means; - control means arranged to determine the deformation of the structure as a function of the value of electromagnetic radiation received.

IPC Classes  ?

• G01D 21/00 - Measuring or testing not otherwise provided for
• G01B 5/30 - Measuring arrangements characterised by the use of mechanical techniques for measuring the deformation in a solid, e.g. mechanical strain gauge
• G01B 7/16 - Measuring arrangements characterised by the use of electric or magnetic techniques for measuring the deformation in a solid, e.g. by resistance strain gauge
• G01L 1/20 - Measuring force or stress, in general by making use of electrokinetic cells, i.e. liquid-containing cells wherein an electrical potential is produced or varied upon the application of stress
• G01M 5/00 - Investigating the elasticity of structures, e.g. deflection of bridges or aircraft wings
• G08C 17/00 - Arrangements for transmitting signals characterised by the use of a wireless electrical link
• G08C 23/00 - Non-electric signal transmission systems, e.g. optical systems
• H04B 5/00 - Near-field transmission systems, e.g. inductive loop type

Abstract

Closure system (4) for connecting two contiguous transport units (2) in a convoy (1) for the transport of goods, the closure system (4) comprising an accordion-shaped element (5) configured to change the length thereof along a longitudinal axis (A) of the convoy (1) and comprising a central portion (5a) and a pair of outer portions (5b) placed on opposite sides with respect to said axis (A), the thickness of the accordion-shaped element (5) decreasing from the central portion (5a) to the outer portions (5b).

IPC Classes  ?

• 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
• B62D 55/24 - Tracks of continuously-flexible type, e.g. rubber belts
• F16C 29/08 - Arrangements for covering or protecting the ways
• B65G 47/66 - Fixed platforms or combs, e.g. bridges between conveyors

Abstract

A handle (10) for opening and closing a door of an aircraft, the handle comprising a base part (14) lockable to a rotatable shaft (11) of an opening mechanism of the door, a hand gripping part (15) connected to the base part (14), and a hinge (13) connecting the base part (14) to the gripping part (15) to allow relative rotation of the gripping part (15) with respect to the base part (14) about a first axis (E). One seat (16) is integral with the base part (14) and at least one other seat (17) is integral with the gripping part (15), the seats being adjacent and aligned along a second axis (F) parallel to the first axis (E). A mechanical fuse element of constraint is received in the seats (16, 17), such that by applying to the gripping part (15) a bending stress around the hinge (13) greater than a predetermined threshold, the element (18) of constraint shears between the seats (16, 17).

IPC Classes  ?

• B64C 1/14 - Windows; Doors; Hatch covers or access panels; Surrounding frame structures; Canopies; Windscreens
• E05B 85/00 - LOCKS; ACCESSORIES THEREFOR; HANDCUFFS - Details of vehicle locks not provided for in groups

Abstract

A roller unit (13) for moving a slat of an aircraft wing is adjustable in height and axial position to adjust the gap (G) between the idle roller (14) and a guide (10) integral with the slat. The roller is carried by an eccentric pin (24) having a stem portion (25) with a threaded portion (31) and an axially grooved end portion (30). A threaded annular element (54) cooperates with the threaded portion (31) of the stem portion to define a desired axial position of the roller. An anti-rotation annular element (57) is coupled in an axially slidable manner with the grooved end portion (30) of the stem portion and may be coupled with the threaded annular element (54) to prevent the rotation thereof on the threaded portion (31) of the stem portion (25). The threaded annular element (54) and the anti-rotation element (57) are tightened together between a pair of nuts (50, 61).

IPC Classes  ?

• B64C 9/22 - Adjustable control surfaces or members, e.g. rudders forming slots at the front of the wing
• B64C 9/02 - Mounting or supporting thereof
• F16C 23/06 - Ball or roller bearings

Abstract

configDPpilotasset;extcodconfigDPpilotassetextconfigDPpilotassetextsuppmissmissionframeconfigDPpilotassetextmissionframemem,visualmem,visualvisualvisualvisual) and generate a map of the operating environment wherein the training element (300) operates.

IPC Classes  ?

• G09B 9/08 - Simulators for teaching or training purposes for teaching control of vehicles or other craft for teaching control of aircraft, e.g. Link trainer

Abstract

A rotor (3, 3', 3'') for an aircraft (1) is described that has a mast (150), an attenuating device (7, 7', 7'') to attenuate the transmission of vibrations from the mast (150) in a plane orthogonal to the first axis (A); and a transmission device (15) interposed between the mast (150) and the attenuating device (7, 7', 7''); the attenuating device (7, 7', 7'') comprises a first and a second mass unit (8, 9) with a first and a second mass (10, 11) rotatable about the first axis (A) with a first and a second rotational speed ((N-1)*Ω; (N+1)*Ω); (N+1)*Ω; (N-1)*Ω)), two control units (40, 40') operable to cause an additional rotation of at least one of the first and second masses (10, 11); and a first and a second support assembly (41, 41'; 42, 42') carrying the first and second masses (10; 11); each control unit (40, 40') controls the angle between the first and second masses (10, 11) and each control unit (40, 40') comprises: a belt (50) coupled to the support assembly (41, 41'; 42, 42') and a drive unit (51, 51') coupled to the first belt (50), to cause the rotation of the first support assembly (41, 41'; 42, 42') with respect to said transmission device (15).

IPC Classes  ?

• B64D 27/00 - Arrangement or mounting of power plant in aircraft; Aircraft characterised thereby

Abstract

A rotor (3, 3') for an aircraft (1) is described that has a mast (50), an attenuating device (7, 7') to attenuate the transmission of vibrations from the mast (50) in a plane orthogonal to the first axis (A), and a transmission device (15) interposed between the mast (50) and the attenuating device (7, 7'); the attenuating device (7; 7') comprises a first and a second mass unit (8, 9) with a first and a second mass (10, 11) rotatable about the first axis (A) with a first and a second rotational speed ((N-1)*Ω; (N+1)*Ω), two control units (40) operable to cause an additional rotation of at least one of the first and second masses (10, 11), and a first and a second support assembly (41, 42) carrying the first and second masses (10, 11); each control unit (40) controls the angle between the first and second masses (10, 11) and comprises a set of drive gear teeth (55, 55') integral with the first support assembly (41, 42), a cogwheel (56) with a set of control gear teeth (57) meshing with the drive gear teeth (55, 55'), and an actuator (58) to cause the rotation of the cogwheel (56) about a second axis (F) and of the first mass (10, 11) about said first axis (A).

IPC Classes  ?

• B64C 27/001 -

Abstract

The apparatus (10) comprises: constraint means (12) adapted to constrain the aircraft part (E); a linear actuator (14) for applying a test load (TL) comprising a tillable first part (24), pivotally constrained about a first and a second geometrical axis (x, y), orthogonal to one another, and a second part (26), slidably mounted on the first part (24) to slide along a longitudinal direction (d); a load cell (16), mounted on the second part (26) to measure a force (F) acting on the aircraft part (E) along said longitudinal direction (d); a first and a second clinometer (18, 20), mounted on the linear actuator (14), and each adapted to measure a respective angle (A, B) representative of the rotation of the linear actuator (14) respectively about the first and second geometrical axis (x, y); a displacement transducer (22), mounted on the first part (24) to measure the slide of the second part (26) relative to the first part (24) of the linear actuator (14).

IPC Classes  ?

• G01M 5/00 - Investigating the elasticity of structures, e.g. deflection of bridges or aircraft wings
• G01M 7/02 - Vibration-testing
• G01M 7/06 - Multidirectional test stands

Abstract

An anti-torque rotor (4) is described comprising: a mast (6) rotatable about a first axis (A); a plurality of blades (8) hinged on the mast (6) and rotatable about respective second axes (B) to vary the respective angles of attack; a control element (16) sliding along the first axis (A) with respect to the mast (6), rotatable with the mast (6) and connected to the blades (8) to cause the rotation about the second axes (B); a control mechanism (10), axially sliding and angularly fixed with respect to the mast (6); and a connection element (17) interposed between the control mechanism (10) and the control element (16), sliding integrally with the control mechanism (10) along the mast (6); the control mechanism (10) comprises a first and a second rod (60, 61); the rotor (4) comprises a coupling (70), which is configured to enable/prevent rotation of the second rod (61) with respect to the first rod (60) when the torque exerted by the first connection element (17) on the second rod (61) about the first axis (A) is greater/less than a threshold value in the event of failure of the connection element (17).

IPC Classes  ?

• 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 27/59 - Transmitting means, e.g. interrelated with initiating means or means acting on blades mechanical

Abstract

An anti-torque rotor (4) is described comprising: a mast (6) rotatable about a first axis (A); a plurality of blades (8) rotatable about respective second axes (B); an element (16) slidable along the first axis (A) with respect to the mast (6), rotating integrally with the mast (6) and operatively connected to the blades (8); a control rod (10) slidable along axis (A); a first bearing (17) with a first ring (30) rotating integrally with element (16), a second ring (31) radially internal to the first ring (30) with respect to the first axis (A) and a plurality of first rolling bodies (32); a third ring (50) sliding integrally with the control rod (10) along the first axis (A) and angularly fixed with respect to the first axis (A); and a locking element (55) arranged in a standard configuration, in which it prevents the relative rotation of the second and third rings (31, 50) and movable from the standard configuration to at least one emergency configuration, in which it renders the second ring (31) free to rotate with respect to the third ring (50), when the first bearing (17) is in a failure condition.

IPC Classes  ?

• 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 27/605 - Transmitting means, e.g. interrelated with initiating means or means acting on blades mechanical including swash plate, spider or cam mechanisms

Abstract

An anti-torque rotor (4) is described for a helicopter (1), comprising: a mast (6) rotatable about a first axis (A); a plurality of blades (8) hinged on the mast (6), extending along respective second axes (B) transversal to said first axis (A) and rotatable about respective said second axes (B) to alter the respective angles of attack; a control element (16) sliding and rotating with respect to the mast (6), and operatively connected to said blades (8) to cause the rotation of said blades (8) about respective second axes (B) following a translation of said element (16) along the first axis (A); a control rod (10) sliding axially along first axis (A) with respect to the mast (6) and angularly fixed with respect to the first axis (A); and a connection element (17) interposed between the control rod (10) and the control element (16), sliding along the first axis (A) with respect to the mast (6) and integrally with the control rod (10); the anti-torque rotor (4) further comprises an interface (18, 93) made of an antifriction material interposed between said control rod (10) and said connection element (17).

IPC Classes  ?

• 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 27/59 - Transmitting means, e.g. interrelated with initiating means or means acting on blades mechanical
• B64C 27/605 - Transmitting means, e.g. interrelated with initiating means or means acting on blades mechanical including swash plate, spider or cam mechanisms
• 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 11/32 - Blade pitch-changing mechanisms mechanical
• F16C 39/02 - Relieving load on bearings using mechanical means
• F16C 21/00 - Combinations of sliding-contact bearings with ball or roller bearings, for exclusively rotary movement
• F16C 19/52 - Bearings with rolling contact, for exclusively rotary movement with devices affected by abnormal or undesired conditions
• B64C 27/54 - Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement

Abstract

An anti-torque rotor (4, 4') is described that comprises: a mast (6) rotatable about a first axis (A); a plurality of blades (8) extending along respective second axes (B); a control element (16) sliding along the first axis (A) with respect to the mast (6), integrally rotatable with said mast (6), and connected to said blades (8); a control rod (10) sliding axially along first axis (A) and angularly fixed with respect to said first axis (A); a connection element (17) interposed between the control rod (10) and the control element (16), sliding along the first axis (A) integrally with the control rod (10), and configured to enable the relative rotation of said control element (16) with respect to the control rod (10) about the first axis (A); and a transmission unit (45) available in an active configuration or an inactive configuration; the transmission unit (45), in turn, comprises: an annular ridge (61) axially and angularly integral with the control rod (10) and radially projecting from the control rod (10); and a seat (64) engaged by the ridge (61) and angularly integral with the control element (16).

IPC Classes  ?

• 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
• B64C 27/12 - Rotor drives

Abstract

A rotor (3) for a hover-capable aircraft (1) is described that comprises: a hub (5) rotating about an axis (A) and, in turn, comprising a plurality of blades (9), a mast (6) connectable to a power unit of the aircraft (1) and operatively connected to the hub (5) to drive the hub (5) in rotation about said axis (A), and an attenuating device (15) to attenuate the transmission of vibrations from the mast (6) to the aircraft (1) parallel to said (A); the attenuating device (15), in turn, comprising a casing (20), a first mass (21) free to oscillate parallel to said axis (A) with respect to the casing (20) and elastically connected to the casing (20), a second mass (25) free to oscillate parallel to said axis (A), connection means (30) adapted to make the first and second masses (21, 25) integrally movable along said axis (A) when the angular speed (Ω) of the mast (6) assumes a first value (Ω1), and actuator means (35) activatable to decouple the first and second masses (21, 25) when the angular speed (Ω) of the mast (6) assumes a second value (Ω2), different from the first value (Ω1).

IPC Classes  ?

• B64C 27/00 - Rotorcraft; Rotors peculiar thereto
• F16F 15/26 - Compensation of inertia forces of crankshaft systems using solid masses, other than the ordinary pistons, moving with the system
• F16F 7/10 - Vibration-dampers; Shock-absorbers using inertia effect
• F16F 7/116 - Vibration-dampers; Shock-absorbers using inertia effect the inertia member being resiliently mounted on metal springs

Abstract

An aircraft (1, 1', 1''', 1'''', 1''''', 1'''''', 1''''''', 1'''''''', 1''''''''', 1'''''''''', 1''''''''''', 1'''''''''''', 1''''''''''''') capable of vertical take-off and landing is described, comprising a first propulsion unit (6a, 6b, 6c, 6d, 6e, 6f; 6a, 6b, 6g', 6h', 6c, 6d, 6e, 6i', 6j', 6f; 6a, 6c; 6d, 6f) configured to generate a first thrust (T1, T2, T3, T4, T5, T6; T1, T2, T7, T8, T3, T4, T5, T9, T10, T6; T1, T3, T4, T6) directed along a first axis (E, F, G, H, I, J; E, F, K, L, G, H, I, M, N, J; E, G, H, J); a second propulsion unit (6a, 6b, 6c, 6d, 6e, 6f; 6a, 6b, 6g', 6h', 6c, 6d, 6e, 6i', 6j', 6f; 6a, 6c; 6d, 6f) configured to generate a second thrust (T1, T2, T3, T4, T5, T6; T1, T2, T7, T8, T3, T4, T5, T9, T10, T6; T1, T3, T4, T6) directed along a second axis (E, F, G, H, I, J; E, F, K, L, G, H, I, M, N, J; E, G, H, J); the first propulsion unit and the second propulsion unit (6a, 6b, 6c, 6d, 6e, 6f; 6a, 6b, 6g', 6h', 6c, 6d, 6e, 6i', 6j', 6f; 6a, 6c; 6d, 6f) can be operated independently of one another; the first axis and second axis (E, F, G, H, I, J; E, F, K, L, G, H, I, M, N, J; E, G, H, J) are inclined to one another with respect to a first longitudinal direction (Y) of the aircraft (1, 1', 1''); the first axis and the second axis (E, F, G, H, I, J; E, F, K, L, G, H, I, M, N, J; E, G, H, J) are fixed with respect to the aircraft (1, 1', 1'').

IPC Classes  ?

• B64C 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
• B64C 27/20 - Rotorcraft characterised by having shrouded rotors, e.g. flying platforms
• B64C 27/26 - Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings