The coherent beam recombination (CBC) system (1) provides an output recombined beam (2) and comprises: a laser source (3) providing a source beam (8) with linewidth; a beam broadener (5) providing a broadened beam (10) from the source beam; a splitter (7) splitting the broadened beam into a plurality of secondary beams (12A-12D); a plurality of channels (20A-20D) coupled to the splitter. Each channel receives a respective secondary beam (12A-I2D) and provides a respective intermediate beam (21A-21D). Each channel has an optical amplifier (40), a phase modulator (42), an optical delay line (44), and an opto-mechanical element (47). The CBC system further comprises an optical sensor (23, 24) that provides a detection signal (TNT, IMG) indicative of an intensity of a received optical beam; a focusing optics (17) that receives the intermediate beams (21A- 21D), provides the output recombined beam (2) from a first portion of each intermediate beam, and provides a sampled recombined beam (63) to the optical sensor from a second portion (63) of each intermediate beam. The CBC system further comprises a control unit (30) coupled to the optical sensor and the plurality of channels. The control unit comprises a phase-locking module (26) configured to: provide a plurality of phase control signals (m, U2, U3, U4) to the phase modulators (42); receive the detection signal (INT) from the optical sensor, indicative of an intensity of the sampled recombined beam; calculate a cost function (J) from the detection signal (INT), wherein the cost function is a function of the intensity of the sampled recombined beam; perform an optimization algorithm of the cost function, configured to maximise the intensity of the sample recombined beam; and provide a plurality of updated phase control signals, based on a result of the optimization algorithm.
H01S 3/10 - Controlling the intensity, frequency, phase, polarisation or direction of the emitted radiation, e.g. switching, gating, modulating or demodulating
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.
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.
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).
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).
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).
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
7.
SERIES OF CONVERTIBLE AIRCRAFTS CAPABLE OF HOVERING AND METHOD FOR CONFIGURING A CONVERTIBLE AIRCRAFT CAPABLE OF HOVERING
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).
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).
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.
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
10.
A SYSTEM FOR SENSING AND RECOGNIZING ACOUSTIC AND/OR VIBRATIONAL ANOMALIES ASSOCIATED WITH A SITE TO BE MONITORED
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.
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.
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).
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.
B29C 70/38 - Automated lay-up, e.g. using robots, laying filaments according to predetermined patterns
B29C 53/04 - Bending or folding of plates or sheets
B29C 70/44 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
B29C 70/46 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs
B29C 70/54 - Component parts, details or accessories; Auxiliary operations
The invention concerns an active electronically steerable antenna (20, 30, 40, 7, 100, 200, 300, 400) including: a planar or quasi-planar radiating array configured to transmit and/or receive radiofrequency or microwave signals, and a plurality of three-dimensional U-shaped modules (1, 2, 3, 5, 81, 82, 301), each arranged behind, and coupled to, a respective planar or quasi-planar radiating subarray of N radiating elements (502) arranged in two rows or columns, each of N/2 radiating elements (502), N being an even integer. Each three-dimensional U-shaped module (1, 2, 3, 5, 81, 82, 301) comprises: a respective base wall (11, 57); two respective side walls (12, 13, 51) that are orthogonally arranged with respect to the respective base wall (11, 57) so as to form therewith a respective three-dimensional U-shaped structure, and are arranged, each, behind a respective row or column of N/2 radiating elements (502) of the respective planar or quasi-planar radiating subarray; and respective transmit and/or receive electronics distributed on said respective base (11, 57) and side walls (12, 13, 51) and configured to implement N respective transmit and/or receive modules. For each three-dimensional U-shaped module (1, 2, 3, 5, 81, 82, 301), the respective transmit and/or receive electronics includes: for each respective side wall (12, 13, 51), N/2 respective transmission and/or reception front-end modules (59, 6) that are mounted on said respective side wall (12, 13, 51), are coupled to the N/2 radiating elements (502) of the respective row or column of the respective planar or quasi-planar radiating subarray, and are configured to implement power amplifiers (121, 131, 92), low noise amplifiers (122, 132, 93), and switches or circulators (122, 132, 91); and respective base wall electronics mounted on the respective base wall (11, 57), connected to the N 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.
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
15.
PROCESS FOR MANUFACTURING A STRUCTURAL COMPONENT IN COMPOSITE MATERIAL STIFFENED WITH AT LEAST ONE STRINGER
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).
B29C 70/54 - Component parts, details or accessories; Auxiliary operations
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
B29C 70/88 - Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts characterised primarily by possessing specific properties, e.g. electrically conductive or locally reinforced
B32B 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 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
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.
B29C 70/54 - Component parts, details or accessories; Auxiliary operations
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
B29C 70/88 - Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts characterised primarily by possessing specific properties, e.g. electrically conductive or locally reinforced
B32B 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 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
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).
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
18.
METHOD OF REALIZATION OF AN ITEM FOR AERONAUTICAL APPLICATION WITH HYBRID COMPOSITE MATERIALS BY MEANS OF ADDITIVE TECHNOLOGY
A method of realization of an aeronautical item with hybrid composite materials by means of additive technology comprising the steps of: design of the product by means of a three-dimensional mathematical model which defines, in a reference system, the shape and dimensions and includes the information associated with the areas of the item that must be reinforced according to the level of stress; deposition, by means of additive technology, of a matrix in polymeric material and of reinforcing fibers according to the mathematical model; deposition of one or more continuous fibers made of different materials along articulated paths in correspondence with the areas that must be reinforced according to the level of stress (continuous fibers oriented along paths defined by the directions of the loads or in any case in the directions provided in the design phase).
B33Y 50/00 - Data acquisition or data processing for additive manufacturing
B33Y 50/02 - Data acquisition or data processing for additive manufacturing for controlling or regulating additive manufacturing processes
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]
B64F 5/10 - Manufacturing or assembling aircraft, e.g. jigs therefor
An electronic tool monitoring system to monitor usage and wear of tools for mechanical machining, comprising, for each tool to be rnonitored: - a tag to be applied to the tool and with a unique identifier that allows the tool to be distinguished from other tools, and - a self-contained and stand-alone electronic monitoring device designed to be firmly and removably applicable to a tool driving apparatus of the tool to monitor usage and wear of a tool. The self-contained and stand-alone electronic monitoring device cornprises: - a electronic sensory arrangement to allow the tool to be identified and usage and wear thereof to be monitored; - an electronic communication interface to communicate with a remote tool management centre, - an electronic operator interface to provide an operator with information on the tool and - an electronic control u.nit electrically connected to the electronic sensory arrangement, the electronic communication interface and the electronic operator in terrace and pro gra m m cd to: o store data indicative of a service life of the tool, ^ identify and monitor usage and wear of the tool based on an output of the electronic sensoiy arrangement, " estimate residual service life of the tool based on monitored usage and wear of the tool and on the stored data indicative of service life of the toot, - if service life of the tool is determined not to be exhausted, provide the operator with information on the residual service life of the tool via the electronic operator inteiTace, - if service life of the tool is determined to be exhausted, implement one or rnore of the following interventions to cause operation of the tool to be interrupted: = notify the operator, via the deetronic operator interface, of a need for operation of the tool to be interrupted, and " intervene directly on the tool driving apparatus of the tool to interrupt operation thereof; and - transmit to the tool management centre, via the electronic communication interface, the unique identifier of the tag associated with the tool and data indicative of either the estimated residual service life of the tool or exhaustion of the service life of the tool.
B23Q 17/00 - Arrangements for indicating or measuring on machine tools
B23B 49/00 - Measuring or gauging equipment on boring machines for positioning or guiding the drill; Devices for indicating failure of drills during boring; Centring devices for holes to be bored
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).
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).
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
The invention relates to a method for manufacturing a box-shaped monolithic structure having a cavity by subjecting to a curing operation a fiber-reinforced prepreg material. The method comprises the step of using two or more support tools that are elongated and internally hollow, having a conformation complementary to that of the cavities to be manufactured and a composition based on reinforcement material and polymer suitable to allow the passage from a rigid state to a flexible elastomeric state and vice versa in response to heating/cooling down; the support tools allow, in the rigid state, the direct lamination of the prepreg material on their external walls and are configured to set the flexible elastomeric state at a temperature lower than the curing temperature and higher than 5000; during the curing operation, the curing pressure is applied both outside the structure being formed and inside the support tools, whose walls have become flexible, push on the prepreg material to be cured. Main Figure: 5
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).
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).
B65G 47/94 - Devices for flexing or tilting travelling structures; Throw-off carriages
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
B65G 47/74 - Feeding, transfer, or discharging devices of particular kinds or types
The invention relates to a method for manufacturing a composite aircraft window frame; the method comprises the steps of: a) positioning in a mold a preform made of pre- impregnated material including dispersed fibers, with a predefined orientation, in a thermosetting resin matrix; b) closing the mold so as to define a gap between at least one surface of said preform and a portion of said mold; c) injecting thermosetting resin into the closed mold through an inlet opening of the mold itself, so as to fill the gap and completely lap said surface of the preform; and d) applying a uniform hydrostatic pressure on the surface by the injection of the resin.
B64F 5/10 - Manufacturing or assembling aircraft, e.g. jigs therefor
B29C 70/36 - 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 and impregnating by casting, e.g. vacuum casting
A system (10) for evaluating an operator in a training mission on a training element (300), including a first processing unit (13) configured to receive and process first data (dconfig, dDP, dpilot, dasset; dext,cod) to generate converted data (dconfig', dDP', dpilot' dasset' dext') according to an operating frequency (f); a second processing unit (15) configured to receive and process the converted data (dconfig', dDP', dpilot', dasset'; dext') and mission support data (dsupp,miss) according to the operating frequency (f) to generate second data (dmission, dframe) and a third processing unit (17) configured to receive and compare the converted data (dconfig' dDP', dpilot', dasset'; dext') with the second data (dmission, dframe) according to the operating frequency (f) such to generate, based on said comparison, response data (dmem, dvisual)· Response data (dmem, dvisual) comprise visualisation data (dvisual) and the evaluation system (10) further includes a graphic process unit (21) configured to receive visualisation data (dvisual) and generate a map of the operating environment wherein the training element (300) operates.
G09B 9/08 - Simulators for teaching or training purposes for teaching control of vehicles or other craft for teaching control of aircraft, e.g. Link trainer
G09B 9/24 - Simulators for teaching or training purposes for teaching control of vehicles or other craft for teaching control of aircraft, e.g. Link trainer including display or recording of simulated flight path
27.
COMPRESSION MOLDING DEVICE OF PARTS IN COMPOSITE MATERIAL STARTING FROM PLATES IN COMPOSITE WITH A THERMOPLASTIC MATRIX
A compression molding device configured for the production of a part in composite material starting from a plate in composite with a thermoplastic matrix is described; the device comprises: a fixed support structure; an upper half-die provided with a first contoured surface corresponding to the profile of an upper surface of the part to be made; a lower half-die provided with a second contoured surface corresponding to the profile of a lower surface of the part to be made; holding means carried by the support structure and configured to hold the plate in a position interposed between the half-dies; and moving means for moving at least one of the half-dies from and towards the plate; the holding means comprise two or more releasable grippers gripping by friction distinct portions of the peripheral edge of the plate and configured to completely release or allow the complete release of the plate itself when the latter is compressed between the half-dies during molding.
The invention relates to a process for obtaining carbon dioxide from furnace combustion fumes, comprising removing the water vapour occurring in the combustion fumes through successive gas compression and expansion steps; separating the carbon dioxide from oxygen and nitrogen through the use of a filter comprising a gas-separating material, such as, for example, fullerenes, zeolites or others, to obtain substantially pure gaseous carbon dioxide; subsequently optionally producing dry ice through further steps of compression and expansion of the substantially pure gaseous carbon dioxide obtained in the preceding steps.
B01D 53/02 - Separation of gases or vapours; Recovering vapours of volatile solvents from gases; Chemical or biological purification of waste gases, e.g. engine exhaust gases, smoke, fumes, flue gases or aerosols by adsorption, e.g. preparative gas chromatography
29.
APPARATUS FOR CARRYING OUT LOAD TESTING ON AN AIRCRAFT PART AND METHOD THEREOF
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).
The actuation system (2) comprises a breechblock assembly (3), a slide (5) whereon the breechblock assembly (3) is mounted, a linear guide whereon said slide (5) is configured to slide linearly, and a cylindrical cam (4) configured to be rotatably actuated by a motor and cooperating with the slide (5) for controlling the movement along the linear guide. The outer surface of the cam (4) defines a path (42) having a first parking section (42a), a second parking section (42b), a forward intermediate section (42c) and a backward intermediate section (42d) connecting the first annular parking section (42a) and said second annular parking section (42b). The slide (5) is moved forward from the first operating position to the second operating position and, respectively, backward from the second operating position to the first operating position.
F41A 7/10 - Drives for externally-powered guns, i.e. drives for moving the breech-block or bolt by an external force during automatic firing using a rotating cylindrical drum having a camming groove
Breechblock assembly (3) for a firearm (1), comprising: a guiding element (31), in turn comprising a slide (314) adapted to slide along a guide (142) comprised in an actuation system (14) of the breechblock assembly (3) driven by a motor; a shutting element (35), adapted to shut an opening in a breech ring (12) of the firearm (1); and a percussion pin (34), which is pushed by an elastic element (332). The shutting element (35) comprising an axial hole (352) in which said percussion pin (34) is adapted to slide along a longitudinal axis (X), as a function of the firing cycle of the firearm (1) with which said breechblock assembly (3) may be associated. The percussion pin (34) being so shaped as to partially come out of said axial hole (352) of the shutting element (35) for firing a piece of ammunition. The breechblock assembly (3) comprises a control system (4) for controlling the percussion pin (34). The control system (4) being adapted to control the operability and the movement of the percussion pin (34) independently of a firing cycle of the firearm (1).
The system (10) comprises a movable assembly (12) configured for pushing a piece of ammunition (A) into a breech ring (2) of a firearm (1) and/or closing the breech ring (2), under control of a motor (M). There is a feeding device (16) configured for feeding the piece of ammunition (A) into a position situated between the movable assembly (12) and the breech ring (2). A synchronization device (20) is included which co-operates with the motor (M) on one side and with the feeding device (16) on the other side. The synchronization mechanism (20) allows for selective transmission of motion, under control of the movable assembly (12), from the motor (M) to the feeding mechanism (16), when said movable assembly (12) is in a position away from the breech ring (2).
F41A 7/10 - Drives for externally-powered guns, i.e. drives for moving the breech-block or bolt by an external force during automatic firing using a rotating cylindrical drum having a camming groove
F41A 9/02 - Feeding of unbelted ammunition using wheel conveyors, e.g. star-wheel-shaped conveyors
Door for cargo airplane, wherein a cargo compartment is accessible from the outside of the fuselage through an opening for loading goods provided with the door. The door is provided with a first operating handle accessible from the outside of the door and used to lock/unlock the pins that are used to connect the door to the fuselage and control the closing/opening of a ventilation door; and a second operating handle accessible from the outside of the door for advancing/retracting the pins in/from respective seats. According to the invention, the door is provided with a third handle accessible from the inside of the door and mechanically interconnected with the first handle for locking/unlocking the pins and controlling the closing/opening of the ventilation door; and a fourth operating handle accessible from the inside of the door and mechanically interconnected with the second handle for advancing/retracting the pins in/from respective seats.
A composite material, in particular for aeronautical applications, comprising : a first pre- impregnated layer (2) having a resin-based matrix (3) reinforced with fibres (4) to give the first layer (2) predefined mechanical properties; and a second layer (6, 6') of magnetic field intensifier material, superimposed on a face (5) of the first layer (2) and joined to the first layer (2) along that face (5); the second layer (6, 6') comprises electrically conductive fibres (7), preferably of carbon, dispersed in the second layer (6, 6') in at least two directions with different orientations and having eguivalent electrical resistivity, parallel to the aforementioned face (5), of less than 600 µOm, preferably less than 200 µOm and even more preferably less than 100 µOm, so as to facilitate localized heating by electromagnetic induction; the first and second layers (2; 6, 6') joined together define a lamina (L, L' ) of super- weldable composite material.
B32B 5/02 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by structural features of a layer comprising fibres or filaments
B32B 5/12 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by structural features of a layer comprising fibres or filaments characterised by the relative arrangement of fibres or filaments of adjacent layers
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 37/06 - Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the heating method
35.
ELECTROMAGNETIC INDUCTION WELDING DEVICE FOR JOINING COMPOSITE MATERIALS AND RELATIVE JOINING METHOD
A portable welding device comprising: a base facing a work surface, in turn designed to receive tapes in electrically conductive composite materials to be joined or defined by at least one already positioned tape; an operating head receiving one tape at a time and movable with respect to the base along at least a first movement line parallel to the work surface; a motorized arm connecting the operating head to the base and selectively activatable to impart movements to the operating head; and feeding means selectively activatable to feed one tape at a time to the operating head and connected to the operating head; the operating head comprises a positioning roller receiving a tape at a time; a pressure roller spaced from and aligned with the positioning roller along the first movement line; and an inductor interposed between the positioning roller and the pressure roller with reference to the first movement line.
A hover-capable aircraft (1) is described that comprises a drive unit (10), a rotor (3, 4) and a transmission (5) interposed between the drive unit (10) and the rotor (3, 4); the transmission (5) comprises a gear (9a, 9b, 9c, 9d, 9e); the gear (9a, 9b, 9c, 9d, 9e), in turn, comprises a main body (40) rotatable about a first axis (B) and a plurality of first teeth (13) projecting in a cantilever fashion from the main body (40); the gear (40) comprises a first pair of first rings (50, 51) axially opposite to each other and cooperating with the gear (9a, 9b, 9c, 9d, 9e) so as to exert a radial force on the gear (9a, 9b, 9c, 9d, 9e).
A method for manufacturing a wing box (10) for aircraft, comprising the steps of: a1) arranging, on a curing surface (22), a first panel (12a), made of a composite material, comprising a skin (16) having a first side (16') and a plurality of stringers (18) that extend parallel to a longitudinal direction (x); b) alternately arranging, on said first side (16') of the first panel (12a) along a transverse direction (y), a rib (14), made of non-polymerized composite material - each rib (14) comprising a plate (15), a first pair of flanges (15a) and a second pair of flanges (15b) arranged at opposite ends of said plate (15) - by placing the first pair of flanges (15a) on said first side (16') of the first panel (12a), and a tool (24) - each tool (24) comprising a central part (24a), a bottom part (24b) and a top part (24c), wherein the central part (24a) of each tool (24) is interposed between said bottom part (24b) and said top part (24c) and may be extracted in a transverse direction (y) - between each pair of consecutive ribs (14) and in contact with both; c) arranging a second panel (12b), made of a composite material, comprising a skin (16), having a first side (16'), and a plurality of stringers (18) that extend along a longitudinal direction (x), by putting said second panel (12b) in contact with the second pair of flanges (15b) of each rib (14); d) pulling out the central part (24a) of each tool (24) along the transverse direction (y) and subsequently removing the top part (24c) and the bottom part (24b) of each tool (24); and e) subjecting the first panel (12a), the second panel (12b), and each rib (14) to a curing process in autoclave with vacuum bag, according to a specific pressure and temperature cycle, for curing the non-polymerized components.
An anodization method for corrosion protection of an aluminium or aluminium alloy element used in an aircraft structure, comprising the following steps: a) subjecting the element to a degreasing step by means of an alkaline bath for removing contaminating elements; b) subjecting the element to a subsequent first washing in water; c) subjecting the element to an acid pickling step by dipping the element in an acid solution and then extracting the element from the acid solution and subjecting the element to a subsequent washing in water; d) subjecting the washed element to a subsequent electrochemical treatment step in a tank by dipping the element in a solution of tartaric acid and sulphuric acid; e) subjecting the element to a subsequent washing in water; f) dipping the element in a bath in which a solution of chromium, with an oxidation number of +3, and zirconium ions and fluorides is present, in order to carry out a first post-anodization sealing step; g) extracting the element from the bath of step f) and subjecting it to a subsequent final washing and a subsequent dipping in a tank of boiling water, and then drying the element.
A tail sitter aircraft (1', 1 ") is described, comprising a wing (4) with a closed front section (C); a fuselage (2), from which said wing extends; said fuselage extending parallel to a first axis (Y); said wing being a non-planar wing closed in on itself and without free ends; said wing comprising a first portion (5) projecting from said fuselage, a second portion (6) spaced from said first portion; and - a first and a second connecting section (7), which are interposed between respective ends (8, 9) of said first portion (5) and of said second portion, said first portion and said second portion being parallel to one another and extending parallel to a second axis (X) orthogonal to said first axis (Y), said first axis (Y) being arranged, in use, vertically in a take-off/landing position and inclined with respect to the vertical direction in a cruising position. Said first and a second connecting section extend parallel to a third axis (Z) orthogonal to said second axis and to said first axis, said wing comprising a third portion (30) arranged on the opposite side of said first portion with respect to said second portion and connected to said first portion at their respective ends (32, 8) by first sections (31) extending parallel to said third axis.
B64C 39/06 - Aircraft not otherwise provided for having disc- or ring-shaped wings
B64C 29/02 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis vertical when grounded
B64C 39/08 - Aircraft not otherwise provided for having multiple wings
B64D 27/02 - Aircraft characterised by the type or position of power plant
A tail sitter aircraft (1') is described that comprises: a fuselage (2) arranged vertically in a take-off/landing position and transversely to a vertical direction in a cruising position of the aircraft; a single wing (4); at least two first engines (15a, 15b) configured to exert respective first thrusts directed along respective first axes (A) on the tail sitter; and at least two second engines (15c, 15d) rotating about respective second axes (A) arranged above said first axes (A) of the first engines (15a, 15b), with reference to said cruising position; the at least two second engines being configured to exert respective second thrusts directed along respective second axes (A) on the tail sitter (1'); the first and second engines being carried by the single wing; the single wing comprises a first portion (5) and a second portion (6) mutually staggered from one another; the second portion being arranged above said first portion, with reference to said cruising position; said first portion comprises two half-wings, extending from opposite lateral sides of the fuselage; the wing further comprises a third portion (30) arranged below said first portion (5) with reference to said cruising position of said aircraft.
B64C 29/02 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis vertical when grounded
B64C 39/06 - Aircraft not otherwise provided for having disc- or ring-shaped wings
B64C 39/08 - Aircraft not otherwise provided for having multiple wings
B64D 27/02 - Aircraft characterised by the type or position of power plant
G05D 1/08 - Control of attitude, i.e. control of roll, pitch, or yaw
41.
SYSTEM FOR ENHANCING THE STRUCTURAL RESILIENCE OF AN AIRCRAFT, AND AIRCRAFT COMPRISING SUCH SYSTEM
A damage recovery system of a fuselage of an aircraft, comprising: a tank containing a polyurethane foam; a main duct fluidically coupled to the tank to receive the foam; secondary ducts fluidically coupled to the main duct; and distribution means adapted to allow an outflow of the foam from the secondary ducts. Graphene powder can be mixed and added to the polyurethane foam. In flight, a possible leak (crack or hole) in the fuselage is plugged by the polyurethane foam with graphene powder.
Non-destructive inspection device, comprising: a first structural layer; a second structural layer coupled to the first structural layer; a chamber sealed between the first and second structural layers, containing a gas; and an active region, housed in the chamber, of a Graphene- based material. In a first operating condition, an AC electric current is fed to the active region and generates by thermoacoustic effect a first acoustic wave propagating away from the chamber. In a second operating condition, a second acoustic wave, generated by a reflection of the first acoustic wave, is received at the chamber and causes a variation in pressure and, consequently, a variation in the temperature of the gas contained in the chamber generating, by means of the thermoelectric effect, an electrical signal in the active region.
G01N 29/14 - Investigating or analysing materials by the use of ultrasonic, sonic or infrasonic waves; Visualisation of the interior of objects by transmitting ultrasonic or sonic waves through the object using acoustic emission techniques
B64F 5/60 - Testing or inspecting aircraft components or systems
B64C 1/00 - Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
G01N 37/00 - INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES - Details not covered by any other group of this subclass
G01S 15/88 - Sonar systems specially adapted for specific applications
43.
CERTIFIABLE DETERMINISTIC SYSTEM SOFTWARE FRAMEWORK FOR HARD REAL-TIME SAFETY-CRITICAL APPLICATIONS IN AVIONICS SYSTEMS FEATURING MULTI-CORE PROCESSORS
An avionics system (1) comprising a central processing unit (2) to implement one or more hard real-time safety-critical applications, the central processing unit (2) comprises a multi-core processor (3) with a plurality of cores (4), an avionics system software executable by the multi-core processor (3), a memory (6), and a common bus (8) though which the multi-core processor (3) can access the memory (6); the avionics system (1) is characterized in that the avionics system software is designed to cause, when executed, the cores (4) in the multi-core processor (3) to access the memory (6) through the common bus (8) by sharing bus bandwidth according to assigned bus bandwidth shares.
G06F 13/372 - Handling requests for interconnection or transfer for access to common bus or bus system with decentralised access control using a time-dependent priority, e.g. individually loaded time counters or time slot
44.
TURRET HAVING A MUNITION GUIDANCE DEVICE PROTECTION
The turret (10) comprises a firearm (14), which is configured to shoot munitions; a support assembly (12), which supports the firearm (14) and which is configured to move the firearm (14) about an azimuthal rotation or swivelling axis (Y) and about a zenithal rotation or elevation axis (X); a munition guidance device (22), which is mounted on the support assembly (12) and is configured to direct a precision-guided munition, which is shot by the firearm (14) towards a target; a protection apparatus (24), which is mounted on the support assembly (12) and is configured to assume: a covering condition, in which the protection apparatus (24) hides the munition guidance device (22) on the inside of said support assembly (12), and an opening condition, in which said protection apparatus (24) shows said munition guidance device (22) on the outside of said support assembly (12).
The firearm support system is adapted to be installed in a vehicle, in particular an aircraft; the vehicle comprises a compartment to accommodate the crew, wherein the compartment has: a bearing surface (4), an upper structure (6) rising above the bearing surface (4), and an opening (8), through which a firearm (10) is going to shoot. The support system comprises: an anchoring portion (20), for being fixed to the upper structure (6) and located in the compartment; a mobile support (22), which is coupled to the anchoring portion (20) in a mobile manner, is adapted for receiving the firearm (10), and is able to allow the firearm (10) to move between an operating position, in which the firearm (10) is ready to shoot through the opening (8), and a non-operating position, in which the firearm (10) is retracted.
F41A 23/20 - Gun mountings, e.g. on vehicles; Disposition of guns on vehicles for disappearing guns
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
F41A 27/02 - Control systems for preventing interference between the moving gun and the adjacent structure
F41A 17/08 - Safety arrangements, e.g. safeties for inhibiting firing in a specified direction, e.g. at a friendly person or at a protected area
The firearm support (28) for a firearm comprises: a body (104), which is provided with at least one profile (106, 106a, 106b, 107a, 107b) on its surface; a feeler pin (100), for striking against the profile and for being coupled to the firearm (10) so as to follow the movement of said firearm (10); a support element (108), rotatable around a first axis (z-z) relative to the body (104). The support element (108) is also suited to be coupled to the firearm (10), thus allowing a mutual rotation between said firearm (10) around a second axis (x-x).
F41A 27/02 - Control systems for preventing interference between the moving gun and the adjacent structure
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
F41A 17/08 - Safety arrangements, e.g. safeties for inhibiting firing in a specified direction, e.g. at a friendly person or at a protected area
F41A 23/00 - Gun mountings, e.g. on vehicles; Disposition of guns on vehicles
47.
SIP EXTENSION FOR DMR NETWORKS MATCHING PMR FEATURES
A system comprising: a SIP Proxy Server, and one or more DMR Gateways to interface the SIP Proxy Server with one or more DMR Networks matching Private/professional Mobile Radio (PMR) features; wherein each DMR Gateway is univocally assigned with a SIP ID and is designed to: interpret messages from the SIP Proxy Server to manage DMR signalling/data/voice features toward DMR Terminals, and initiate DMR features on account of DMR Terminals operating under it and make requests for DMR signalling/data/voice features toward destinations belonging to another Network; wherein each DMR Gateway is further designed to: transcode an over-the-air, manufacturer-specific DMR Terminal registration into a SIP REGISTER message to result in the SIP Proxy server perceiving and managing the DMR Terminal as a SIP User Agent; and wherein the SIP Proxy Server is designed to: manage DMR signalling features, including voice call set-up, and DMR data features using the SIP MESSAGE method, and/or manage DMR signalling/data/voice group features.
A communication method of the SMF type for a network (1) of nodes including a multicast group. The method includes the steps, performed by a first node, of: determining (7a) a set of respective multipoint relays; determining (7b) the nodes for which the first node is a multipoint relay; determining (8) a routing table including identifiers of destination nodes and corresponding identifiers of next-hop nodes; receiving (10) a multicast packet sent from a sending node, where the first node is a multipoint relay; checking (22) if, for each node identifier of the multicast group, the entry in the routing table that includes a destination node identifier corresponding to the node identifier of the multicast group contains a next-hop node identifier that corresponds to the sending node, and if the counter contained in the multicast packet respects a relation with a limit; and determining (30; 42) whether to retransmit the multicast packet, on the basis of the outcome of the checking step.
H04W 40/26 - Connectivity information management, e.g. connectivity discovery or connectivity update for hybrid routing by combining proactive and reactive routing
H04W 48/08 - Access restriction or access information delivery, e.g. discovery data delivery
An actuating system of sectors of a device for producing an airplane fuselage in which a lamination mandrel is delimited by an external surface which defines a rotation solid with respect to a symmetry axis and comprises a plurality of sectors angularly spaced about the axis and mobile along guides between: an expanded lamination position; and a contracted disassembling position. Each sector is provided with an actuating system of the screw as a threaded element extending along a rotation axis mounted axially on a portion of shaft and provided externally with a thread. Constraint means are provided between the internal shaft and a tubular portion adapted to prevent angular displacement. A thermal stress applied to the threaded element produces the sliding of a free end portion so that an increase in the temperature does not produce an overall elongation of the threaded element.
There is described a transmission for a helicopter, the transmission having a movable transmission member; a casing housing the movable member; lubricated supporting means for supporting the movable member inside the casing and for rotation about an axis; and feed means for feeding a lubricating fluid to the supporting means; the transmission also has storage means permitting gradual release of the lubricating fluid, and which are connected fluidically to the feed means and to the supporting means to permit lubrication of the supporting means in the event of breakdown of the feed means; and the storage means are angularly integral with the movable member and located radially inwards of the supporting means to feed the lubricating fluid centrifugally to the supporting means.
There is described a helicopter having a first member movable with respect to a second member; lubricated supporting means for supporting the first member with respect to the second member; and a primary lubricating circuit for lubricating the supporting means and in turn having primary storage means for accumulating a lubricating fluid, and primary fluid feed means for feeding the lubricating fluid to the supporting means; the helicopter also has an auxiliary lubricating circuit supplied continually by the primary storage means with a first lubricating fluid flow value, and itself continually supplying the supporting means with a second lubricating fluid flow value lower than the first value, so as to produce an auxiliary storage volume of lubricating fluid for use in the event of breakdown of the primary lubricating circuit.
There is described a rotor for a helicopter, having a hub rotating about a first axis; a number of blades projecting from the hub in respective longitudinal directions lying in a plane crosswise to the first axis, and each connected to the hub so as to be movable at least about a second axis crosswise to the first axis and to the relative longitudinal direction; and a number of damping devices for damping vibration of the helicopter, and each interposed between a respective blade, and the hub; each damping device has a plate member fixed, on one side, to the hub, connected, on the opposite side, to the relative blade by elastic means, and flexible, during movement of the blade, about a third axis coaxial with the second axis.
A helicopter is disclosed. The helicopter comprises a fuselage, a rudder projecting from a tail end of the fuselage and two rear fixed wings located on opposite sides of said fuselage at said rudder. Each of said fixed wings has a free end and a winglet projecting transversely from the free end. The winglet projects completely from an unique side of the wing and comprises a flat underside facing said rudder and an opposite convex topside.
B64C 23/06 - Influencing air flow over aircraft surfaces, not otherwise provided for by generating vortices
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
54.
DEVICE FOR INDICATING A RESIDUAL POWER MARGIN OF AIRCRAFT TURBINE ENGINES
A device for indicating a residual power margin of aircraft turbine engines includes a measuring stage associated with at least one turbine engine of an aircraft to measure a number of first parameters related to a power output of the engine; a calculating unit associated with the measuring unit to calculate at least one second parameter indicating the power output of the engine on the basis of the first parameters; and a display. The display includes a power scale having at least one reference indicator indicating an operating limit of the engine; and at least one cursor cooperating with the power scale and the reference indicator to simultaneously display a current value of the second parameter and an available power margin of the engine.
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
G01D 7/04 - Indicating value of two or more variables simultaneously using a separate indicating element for each variable
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