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 - Commande de l'intensité, de la fréquence, de la phase, de la polarisation ou de la direction du rayonnement, p.ex. commutation, ouverture de porte, modulation ou démodulation
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 - Giravions complexes, c. à d. aéronefs utilisant en vol à la fois les caractéristiques de l'avion et celles du giravion avec hélices propulsives de déplacement pouvant pivoter pour agir comme rotors de sustentation
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 - Mécanismes de commande manuelle équipés d'un seul organe de commande travaillant avec plusieurs organes commandés, p.ex. en sélection ou simultanément l'organe de commande étant manœuvré de différentes manières indépendantes, chacune de ces manœuvres individuelles entraînant un seul organe commandé dans lesquels la manœuvre de l'organe de commande peut être effectuée de plusieurs manières simultanément
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.
G01H 9/00 - Mesure des vibrations mécaniques ou des ondes ultrasonores, sonores ou infrasonores en utilisant des moyens sensibles aux radiations, p.ex. des moyens optiques
11.
METHOD FOR THE MANUFACTURE OF A STRUCTURAL COMPONENT IN COMPOSITE MATERIAL REINFORCED WITH STIFFENING STRINGERS AND STRUCTURAL COMPONENT
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 - Empilage automatisé, p.ex. utilisant des robots, par application de filaments selon des modèles prédéterminés
B29C 53/04 - Cintrage ou pliage de plaques ou de feuilles
B29C 70/44 - Façonnage ou imprégnation par compression pour la fabrication d'objets de longueur définie, c.à d. d'objets distincts utilisant une pression isostatique, p.ex. moulage par différence de pression, avec un sac à vide, dans un autoclave ou avec un caoutchouc expansible
B29C 70/46 - Façonnage ou imprégnation par compression pour la fabrication d'objets de longueur définie, c.à d. d'objets distincts utilisant des moules opposables, p.ex. pour déformer des préimprégnés [SMC] ou des "prepregs"
B29C 70/54 - Façonnage de matières composites, c. à d. de matières plastiques comprenant des renforcements, des matières de remplissage ou des parties préformées, p.ex. des inserts comprenant uniquement des renforcements, p.ex. matières plastiques auto-renforçantes opération de façonnage des matières composites comprenant uniquement des renforcements - Parties constitutives, détails ou accessoires; Opérations auxiliaires
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 - Systèmes de diversité; Systèmes à plusieurs antennes, c. à d. émission ou réception utilisant plusieurs antennes utilisant plusieurs antennes indépendantes espacées à la station d'émission
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 - Façonnage de matières composites, c. à d. de matières plastiques comprenant des renforcements, des matières de remplissage ou des parties préformées, p.ex. des inserts comprenant uniquement des renforcements, p.ex. matières plastiques auto-renforçantes opération de façonnage des matières composites comprenant uniquement des renforcements - Parties constitutives, détails ou accessoires; Opérations auxiliaires
B29C 70/64 - Façonnage de matières composites, c. à d. de matières plastiques comprenant des renforcements, des matières de remplissage ou des parties préformées, p.ex. des inserts comprenant uniquement des matières de remplissage les matières de remplissage ayant une influence sur les caractéristiques de surface du matériau, p.ex. en se concentrant près de la surface ou en étant enfoncées de force dans la surface
B29C 70/88 - Façonnage de matières composites, c. à d. de matières plastiques comprenant des renforcements, des matières de remplissage ou des parties préformées, p.ex. des inserts caractérisées principalement par des propriétés spécifiques, p.ex. électriquement conductrices ou renforcées localement
B32B 5/26 - Produits stratifiés caractérisés par l'hétérogénéité ou la structure physique d'une des couches caractérisés par la présence de plusieurs couches qui comportent des fibres, filaments, grains ou poudre, ou qui sont sous forme de mousse ou essentiellement poreuses une des couches étant fibreuse ou filamenteuse un autre couche également étant fibreuse ou filamenteuse
B32B 13/14 - Produits stratifiés composés essentiellement d'une substance à prise hydraulique, p.ex. du béton, du plâtre, du ciment, ou d'autres matériaux entrant dans la construction adjacente à une couche fibreuse ou filamenteuse
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 - Façonnage de matières composites, c. à d. de matières plastiques comprenant des renforcements, des matières de remplissage ou des parties préformées, p.ex. des inserts comprenant uniquement des renforcements, p.ex. matières plastiques auto-renforçantes opération de façonnage des matières composites comprenant uniquement des renforcements - Parties constitutives, détails ou accessoires; Opérations auxiliaires
B29C 70/64 - Façonnage de matières composites, c. à d. de matières plastiques comprenant des renforcements, des matières de remplissage ou des parties préformées, p.ex. des inserts comprenant uniquement des matières de remplissage les matières de remplissage ayant une influence sur les caractéristiques de surface du matériau, p.ex. en se concentrant près de la surface ou en étant enfoncées de force dans la surface
B29C 70/88 - Façonnage de matières composites, c. à d. de matières plastiques comprenant des renforcements, des matières de remplissage ou des parties préformées, p.ex. des inserts caractérisées principalement par des propriétés spécifiques, p.ex. électriquement conductrices ou renforcées localement
B32B 5/26 - Produits stratifiés caractérisés par l'hétérogénéité ou la structure physique d'une des couches caractérisés par la présence de plusieurs couches qui comportent des fibres, filaments, grains ou poudre, ou qui sont sous forme de mousse ou essentiellement poreuses une des couches étant fibreuse ou filamenteuse un autre couche également étant fibreuse ou filamenteuse
B32B 13/14 - Produits stratifiés composés essentiellement d'une substance à prise hydraulique, p.ex. du béton, du plâtre, du ciment, ou d'autres matériaux entrant dans la construction adjacente à une couche fibreuse ou filamenteuse
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 - Inversion du flux de la soufflante utilisant des volets inverseurs de poussée ou des portes montées sur le carter de la soufflante la partie arrière du carter de la soufflante étant mobile pour découvrir des ouvertures d'inversion de poussée dans le carter de la soufflante
F02K 1/60 - Inversion du jet principal par blocage de l'échappement vers l'arrière à l'aide d'éléments pivotants ayant la forme de paupières ou de coquilles, p.ex. inverseurs du type se trouvant en aval de la sortie de la tuyère en position de fonctionnement
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 - Acquisition ou traitement de données pour la fabrication additive
B33Y 50/02 - Acquisition ou traitement de données pour la fabrication additive pour la commande ou la régulation de procédés de fabrication additive
B29C 64/118 - Procédés de fabrication additive n’utilisant que des matériaux liquides ou visqueux, p.ex. dépôt d’un cordon continu de matériau visqueux utilisant un matériau filamentaire mis en fusion, p.ex. modélisation par dépôt de fil en fusion [FDM]
B64F 5/10 - Fabrication ou assemblage d’aéronefs, p.ex. gabarits à cet effet
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 - Agencements sur les machines-outils pour indiquer ou mesurer
B23B 49/00 - Systèmes de mesure ou de calibrage des machines à aléser, pour le positionnement ou le guidage du foret; Dispositif pour indiquer les défauts des forets pendant l'alésage; Dispositifs à centrer les trous à aléser
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).
B64D 33/08 - Aménagement sur les aéronefs des éléments ou des auxiliaires des ensembles fonctionnels de propulsion, non prévu ailleurs des systèmes de refroidissement des ensembles fonctionnels de propulsion
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 - Giravions; Rotors propres aux giravions caractérisés par l'existence d'un rotor auxiliaire ou d'un dispositif à jet fluide pour contrebalancer le couple du rotor de sustentation ou faire varier la direction du giravion
B64C 39/06 - Aéronefs non prévus ailleurs à ailes en forme de disque ou d'anneau
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 - Dispositifs pour courber ou culbuter les structures en mouvement; Chariots à bascule
B65G 17/06 - Transporteurs comportant un élément de traction sans fin, p.ex. une chaîne transmettant le mouvement à une surface porteuse de charges continue ou sensiblement continue, ou à une série de porte-charges individuels; Transporteurs à chaîne sans fin dans lesquels des chaînes constituent la surface portant la charge avec une surface portante formée par une série de maillons, de plaques ou plates-formes reliés entre eux, p.ex. longitudinaux
B65G 47/74 - Dispositifs d'alimentation, de transfert ou de déchargement de genres ou types particuliers
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 - Fabrication ou assemblage d’aéronefs, p.ex. gabarits à cet effet
B29C 70/36 - Façonnage par empilage, c.à d. application de fibres, de bandes ou de feuilles larges sur un moule, un gabarit ou un noyau; Façonnage par pistolage, c.à d. pulvérisation de fibres sur un moule, un gabarit ou un noyau et imprégnation par coulée, p.ex. coulée sous vide
B64C 1/14 - Fenêtres; Portes; Trappes d'évacuation ou panneaux de visite; Structures de cadres environnants; Verrières; Pare-brise
26.
SYSTEM AND METHOD FOR EVALUATING THE TRAINING OF AN OPERATOR IN A TRAINING MISSION IN REAL TIME
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 - Simulateurs pour l'enseignement ou l'entraînement pour l'enseignement de la conduite des véhicules ou autres moyens de transport pour l'enseignement du pilotage des aéronefs, p.ex. bancs d'entraînement au pilotage sans visibilité
G09B 9/24 - Simulateurs pour l'enseignement ou l'entraînement pour l'enseignement de la conduite des véhicules ou autres moyens de transport pour l'enseignement du pilotage des aéronefs, p.ex. bancs d'entraînement au pilotage sans visibilité comprenant l'affichage ou l'enregistrement de la trajectoire de vol simulée
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.
B29C 43/32 - Moulage par pressage, c. à d. en appliquant une pression externe pour faire couler la matière à mouler; Appareils à cet effet - Eléments constitutifs, détails ou accessoires; Opérations auxiliaires
28.
PROCESS FOR OBTAINING CARBON DIOXIDE FROM FURNACE COMBUSTION FUMES
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 - SÉPARATION Épuration chimique ou biologique des gaz résiduaires, p.ex. gaz d'échappement des moteurs à combustion, fumées, vapeurs, gaz de combustion ou aérosols par adsorption, p.ex. chromatographie préparatoire en phase gazeuse
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 - Mécanismes d'entraînement des armes à feu à moteur externe, c. à d. mécanismes d'entraînement pour déplacer le bloc de culasse pendant le tir automatique en utilisant une force externe utilisant un tambour tournant muni d'une rainure de commande de came
F41A 9/50 - Systèmes d'entraînement ou de commande externes
31.
BREECHBLOCK ASSEMBLY FOR A FIREARM AND RELATED FIREARM
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).
F41A 17/64 - Sûretés de percuteur, c. à d. moyens pour prévenir le mouvement des pièces de percussion coulissantes
F41A 7/08 - Mécanismes d'entraînement des armes à feu à moteur externe, c. à d. mécanismes d'entraînement pour déplacer le bloc de culasse pendant le tir automatique en utilisant une force externe
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 - Mécanismes d'entraînement des armes à feu à moteur externe, c. à d. mécanismes d'entraînement pour déplacer le bloc de culasse pendant le tir automatique en utilisant une force externe utilisant un tambour tournant muni d'une rainure de commande de came
F41A 9/02 - Alimentation en munitions sans bande utilisant des convoyeurs à roues rotatives, p.ex. des convoyeurs à roue à étoiles
F41A 9/42 - Refouloirs indépendants du bloc de culasse
F41A 9/51 - Impulseurs, c. à d. moteurs commandés de l'extérieur
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 - Produits stratifiés caractérisés par l'hétérogénéité ou la structure physique d'une des couches caractérisés par les caractéristiques de structure d'une couche comprenant des fibres ou des filaments
B32B 5/12 - Produits stratifiés caractérisés par l'hétérogénéité ou la structure physique d'une des couches caractérisés par les caractéristiques de structure d'une couche comprenant des fibres ou des filaments caractérisés par la disposition relative des fibres ou filaments des couches adjacentes
B32B 5/26 - Produits stratifiés caractérisés par l'hétérogénéité ou la structure physique d'une des couches caractérisés par la présence de plusieurs couches qui comportent des fibres, filaments, grains ou poudre, ou qui sont sous forme de mousse ou essentiellement poreuses une des couches étant fibreuse ou filamenteuse un autre couche également étant fibreuse ou filamenteuse
B32B 37/06 - Procédés ou dispositifs pour la stratification, p.ex. par polymérisation ou par liaison à l'aide d'ultrasons caractérisés par le procédé de chauffage
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.
B29C 65/14 - Assemblage d'éléments préformés; Appareils à cet effet par chauffage, avec ou sans pressage par énergie ondulatoire ou rayonnement corpusculaire
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 - Aéronefs non prévus ailleurs à ailes en forme de disque ou d'anneau
B64C 29/02 - Aéronefs capables d'atterrir ou de décoller à la verticale, p.ex. aéronefs à décollage et atterrissage verticaux [ADAV, en anglais VTOL] dont l'axe matérialisant la direction du vol est vertical lorsque l'aéronef est au sol
B64C 39/08 - Aéronefs non prévus ailleurs à ailes multiples
B64D 27/02 - Aéronefs caractérisés par le type ou la position des groupes moteurs
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 - Aéronefs capables d'atterrir ou de décoller à la verticale, p.ex. aéronefs à décollage et atterrissage verticaux [ADAV, en anglais VTOL] dont l'axe matérialisant la direction du vol est vertical lorsque l'aéronef est au sol
B64C 39/06 - Aéronefs non prévus ailleurs à ailes en forme de disque ou d'anneau
B64C 39/08 - Aéronefs non prévus ailleurs à ailes multiples
B64D 27/02 - Aéronefs caractérisés par le type ou la position des groupes moteurs
G05D 1/08 - Commande de l'attitude, c. à d. élimination ou réduction des effets du roulis, du tangage ou des embardées
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 - Recherche ou analyse des matériaux par l'emploi d'ondes ultrasonores, sonores ou infrasonores; Visualisation de l'intérieur d'objets par transmission d'ondes ultrasonores ou sonores à travers l'objet utilisant des techniques d'émission acoustique
B64F 5/60 - Test ou inspection des composants ou des systèmes d'aéronefs
B64C 1/00 - Fuselages; Caractéristiques structurales communes aux fuselages, voilures, surfaces stabilisatrices ou organes apparentés
G01N 37/00 - RECHERCHE OU ANALYSE DES MATÉRIAUX PAR DÉTERMINATION DE LEURS PROPRIÉTÉS CHIMIQUES OU PHYSIQUES - Détails non couverts par les autres groupes de la présente sous-classe
G01S 15/88 - Systèmes sonar, spécialement adaptés à des applications spécifiques
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 - Gestion de demandes d'interconnexion ou de transfert pour l'accès au bus ou au système à bus communs avec commande d'accès décentralisée utilisant une priorité dépendant du temps, p.ex. des compteurs de temps individuellement chargés ou des tranches de temps
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 - Supports d'armes à feu, p.ex. sur des véhicules; Disposition des armes à feu sur des véhicules pour des armes à feu à éclipses
B64D 7/06 - Agencement à bord aéronefs des équipements militaires, p.ex. des armes, des accessoires d'armement ou des blindages de protection; Adaptations des installations d'armement aux aéronefs les armes étant des armes à feu mobiles
F41A 27/02 - Systèmes de commande pour empêcher une arme à feu de heurter une partie de son propre support pendant le mouvement de pointage
F41A 17/08 - Mécanismes de sûreté, p.ex. sûretés pour empêcher le tir dans une direction prédéterminée, p.ex. le tir sur une personne amie ou le tir sur une aire protégée
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 - Systèmes de commande pour empêcher une arme à feu de heurter une partie de son propre support pendant le mouvement de pointage
B64D 7/06 - Agencement à bord aéronefs des équipements militaires, p.ex. des armes, des accessoires d'armement ou des blindages de protection; Adaptations des installations d'armement aux aéronefs les armes étant des armes à feu mobiles
F41A 17/08 - Mécanismes de sûreté, p.ex. sûretés pour empêcher le tir dans une direction prédéterminée, p.ex. le tir sur une personne amie ou le tir sur une aire protégée
F41A 23/00 - Supports d'armes à feu, p.ex. sur des véhicules; Disposition des armes à feu sur des véhicules
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 - Gestion d'informations sur la connectabilité, p.ex. exploration de connectabilité ou mise à jour de connectabilité pour acheminement hybride en combinant un acheminement proactif et un acheminement réactif
H04W 48/08 - Distribution d'informations relatives aux restrictions d'accès ou aux accès, p.ex. distribution de données d'exploration
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 - Moyens permettant d'influencer l'écoulement d'air sur les surfaces des aéronefs, non prévus ailleurs par génération de tourbillons
B64C 27/82 - Giravions; Rotors propres aux giravions caractérisés par l'existence d'un rotor auxiliaire ou d'un dispositif à jet fluide pour contrebalancer le couple du rotor de sustentation ou faire varier la direction du giravion
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 - Aménagements ou adaptations des instruments
B64D 45/00 - Indicateurs ou dispositifs de protection d'aéronefs, non prévus ailleurs
G01C 23/00 - Instruments combinés indiquant plus d’une valeur de navigation, p.ex. pour l’aviation; Dispositifs de mesure combinés pour mesurer plusieurs variables du mouvement, p.ex. la distance, la vitesse ou l’accélération
G01D 7/04 - Indication de la valeur de plusieurs variables simultanément utilisant un élément indicateur séparé pour chaque variable
brevets
