The artefact comprises a flat or curved body substantially made of metal or metal alloy or composite material and comprising one or more ice protection panel(s). The ice protection panel(s) comprise a heater film and at least one ply made of CFRC and/or GFRC. The heater film includes a thermoplastic polymeric matrix containing polar groups, and at least one graphene or graphitic layer which is electrically conductive, or a thermosetting resin, and functionalized with elastomeric nanodomains containing dispersed electrical conductive carbon–based nanoparticles. The heater film is also provided of electrodes and is placed between said at least one ply made of CFRC and/or GFRC and an outer protective coating, or is placed between two plies independently made of CFRC and/or GFRC.
H05B 3/14 - Eléments chauffants caractérisés par la composition ou la nature des matériaux ou par la disposition du conducteur caractérisés par la composition ou la nature du matériau conducteur le matériau étant non métallique
B64D 15/12 - Dégivrage ou antigivre des surfaces externes des aéronefs par chauffage électrique
H05B 3/34 - Eléments chauffants ayant une surface s'étendant essentiellement dans deux dimensions, p.ex. plaques chauffantes flexibles, p.ex. grillages ou tissus chauffants
2.
AIRCRAFT CAPABLE OF HOVERING AND RELATIVE CONTROL METHOD
Aircraft (1) capable of hovering comprising a fuselage (2), at least one rotor (3a, 3b, 4) that is rotatable with respect to the fuselage (2), electrical drive means adapted to rotate the rotor (3a, 3b, 4) and electrically powered by a battery (9), and a cooling system (10) of the battery (9). Said cooling system (10) comprises, in turn, a first opening (20) for the air to enter, second openings (21) for the air to escape and a passage (22), which places the first opening (20) in fluidic communication with the second openings (21) and within which the battery (9) is placed. The cooling system (10) further comprises a fan (23) adapted to increase the kinetic energy of the air contained in the passage (22) and which is operated when the forward speed (v) of the aircraft (1) with respect to the ground is lower than a speed threshold value (v0) and/or when the temperature (T) of the battery (9) exceeds a temperature threshold value (T0).
B64D 33/08 - 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
B64D 27/24 - Aéronefs caractérisés par le type ou la position des groupes moteurs utilisant la vapeur, l'électricité ou l'énergie de ressorts
B64D 13/00 - Aménagements ou adaptations des appareils de conditionnement d'air pour équipages d'aéronefs, passagers ou pour emplacement réservé au fret
B64C 29/00 - Aéronefs capables d'atterrir ou de décoller à la verticale, p.ex. aéronefs à décollage et atterrissage verticaux [ADAV, en anglais VTOL]
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
B64D 13/06 - Aménagements ou adaptations des appareils de conditionnement d'air pour équipages d'aéronefs, passagers ou pour emplacement réservé au fret l'air étant climatisé
3.
TURRET, IN PARTICULAR FOR NAVAL APPLICATIONS, PROVIDED WITH A DEVICE FOR MOVING AN AMMUNITION GUIDANCE SYSTEM
The turret, in particular for naval applications, comprises a traversing part and an elevating part integrally rotatable with the traversing part. There is a barrel supported by the elevating part and integrally rotatable therewith about the elevation axis (X1). The barrel is configured to fire guided ammunition through itself. An ammunition guidance system (24) is configured to direct a guided piece of ammunition towards a target by means of an electromagnetic emission. A moving device (100), whereon the ammunition guidance system (24) is mounted, is configured to move the latter in such a way as to orient the electromagnetic emission towards the target. The moving device (100) is mounted to the traversing part (14) and comprises a frame (102) that rotatably supports the ammunition guidance system (24) about an azimuthal or traversing movement axis (Y1) and a zenithal or elevation movement axis (X1).
Fire fighting drone comprising an exoskeleton (2) defining an internal space (3) extending along an axis H and a flexible bag (4) stably housed in the internal space (3), provided with a release valve (6) and configured to contain a fire fighting liquid (7); a support structure (8) provided with a plurality of thrusters (11) adapted to perform a thrust that enables the support structure (8) to be supported in flight; the support structure (8) is connected to a first end portion (2-a) of the exoskeleton (2); a plurality of movable directional wings (10) carried by the exoskeleton (2), extending outwards from the exoskeleton itself and angularly movable relative to the exoskeleton (2) around respective axes H transverse to the axis H; an electronic control unit adapted to control the thruster (11), to generate the release signal and adapted to control the actuators that perform the rotation of the wings; the electronic control unit is configured to control said wings to allow the rotation of the wings during the free-fall phase of said drone which is released from an aircraft and thereby performs a certain trajectory of said drone from the aircraft to a launch zone; the electronic unit is configured to enable the discharge of said liquid from said bag and the activation of the thrusters (11) following the discharge of the liquid to enable the flight of the support structure and of the exoskeleton containing the empty bag to a landing zone.
The turret (10), in particular for naval applications, comprises a traversing part (14) and an elevating part (16) integrally rotatable with the traversing part (14). There is a barrel (18) supported by the elevating part (16) and integrally rotatable therewith about the elevation axis (X). The barrel (18) is configured to fire guided ammunition through itself. An ammunition guidance system (24) is configured to direct a guided piece of ammunition towards a target by means of an electromagnetic emission. A protection device (26) is provided, which is configured to assume a closing condition, wherein it encloses and protects the ammunition guidance system (24), and an opening condition, wherein it clears and exposes the ammunition guidance system (24). The ammunition guidance system (24) and the protection device (26) are mounted to the traversing part (14). The traversing part (14) internally defines a reclosable cavity (28) that houses the ammunition guidance system (24), faces forwards, and is configured to be closed by the protection device (26) when the latter is in the closing condition.
An aircraft (1) comprising a fuselage (2, 2', 2'') with a nose (4) and a tail (5) arranged on opposite parts to each other along a first longitudinal axis (Y) is described; a pair of half-wings (3) arranged on respective mutually opposite sides of the fuselage (2, 2', 2'); a first and a second rotor (22a, 22b) carried by respective half-wings (3), respectively rotatable around a second and third axis (F, G) inclinable with respect to said fuselage (2, 2', 2''), and independently operable from each other; the aircraft (1) is switchable between a first hovering flight or take-off/landing configuration wherein the fourth and fifth axis (F, G) are arranged orthogonal to said first axis (Y); and a second forward flight configuration wherein the fourth and fifth axis (F, G) are arranged parallel or inclined with respect to said first axis (Y); the aircraft (1) further comprising a tail portion (6) comprising a first aerodynamic surface (8), and a third and a fourth rotor (21a, 21b) rotatable around a fixed fourth and a fifth axis (D, E); and support means (31a, 31b) of the third and fourth rotor (21a, 21b) connected to a corresponding said half-wing (3) and to a corresponding said fin (52).
A fuselage (2, 2', 2'') for a convertible aircraft (1) is described, comprising a nose (4) and a tail (5) arranged on mutually opposite sides along a first longitudinal axis (Y) of the fuselage (2); a first portion (100) and a second portion (101) arranged one after the other, proceeding along the first axis (Y) from the nose (4) towards the tail (5); and an electric power source (102) connectable with at least one electric powertrain (40a, 40b, 40c, 40d, 40e, 40f) and arranged inside the second portion (101); the first and second portion (100, 101) define respectively a first and a second section (110, 111, 111'') in a plane orthogonal to the first axis (Y); the second section (111) defines at least one air intake (120) that is open towards the outside of the fuselage (2) itself and fluidically connected with the source (102) so as to convey, in use, a flow of cooling air onto the source (102) itself following the forward motion of the aircraft (1); the second section (111, 111'') having a larger area than the first section (110); the air intake (120) being arranged at a sidewall (19) of the second portion (101) and externally to the first portion (100) and in a view parallel to the first axis (Y).
B64D 27/24 - Aéronefs caractérisés par le type ou la position des groupes moteurs utilisant la vapeur, l'électricité ou l'énergie de ressorts
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
B64C 29/00 - Aéronefs capables d'atterrir ou de décoller à la verticale, p.ex. aéronefs à décollage et atterrissage verticaux [ADAV, en anglais VTOL]
B64C 7/00 - Structures ou carénages non prévus ailleurs
B64C 1/14 - Fenêtres; Portes; Trappes d'évacuation ou panneaux de visite; Structures de cadres environnants; Verrières; Pare-brise
B64C 1/00 - Fuselages; Caractéristiques structurales communes aux fuselages, voilures, surfaces stabilisatrices ou organes apparentés
B64U 101/61 - Véhicules aériens sans pilote spécialement adaptés à des utilisations ou à des applications spécifiques au transport de marchandises autres que des armes au transport de passagers
8.
METHOD FOR IDENTIFYING MALFUNCTION CONDITIONS OF SENSORS THAT MEASURE THE AMOUNT OF FUEL IN THE TANKS OF AN AIRCRAFT
Method for identifying malfunction conditions of the sensors that measure the amount of fuel in the tanks of an aircraft (1) provided with at least one first tank (2/6) arranged on a first side of the aircraft and at least one second tank (4/8) arranged on a second side, each first and second tank (2/6; 4/8) is provided with a plurality m of sensors (11) detecting the level of fuel within the respective tank (2/6 and 4/8). The method performs a symmetry control wherein the level gradients (11) associated with the first tank (2/6) and the second tank (4/8) are compared to each other; and if the values of the compared gradients are close, a consistency condition is detected. As an alternative to the symmetry control, a discontinuity control is carried out wherein the step of comparing the consumption gradient associated with each sensor (11) with a reference gradient comprising an average consumption gradient of the other sensors and/or with the total consumption gradient is carried out.
G01F 25/20 - Test ou étalonnage des appareils pour la mesure du volume, du débit volumétrique ou du niveau des liquides, ou des appareils pour compter par volume des appareils pour mesurer le niveau des liquides
B64D 37/00 - Aménagements relatifs à l'alimentation des groupes moteurs en carburant
9.
EQUIPMENT AND PROCESS FOR MAKING A STRUCTURAL ELEMENT IN COMPOSITE MATERIAL
The invention relates to equipment (10) for making a structural element (1) of composite material having a longitudinal axis (A) and an axial cavity (2). The equipment (10) comprises a support frame (11) and a laminating mandrel (12), which is mounted on the support frame (11) so that it can rotate about its own central axis (B) and defines an outer laminating surface (13); the support frame (11) comprises two vertical headers (14, 15), facing each other and parallel to each other, and longitudinal connecting means (16) for longitudinally connecting the headers (14, 15); each header (14, 15) comprises a fixed portion (17) and a movable portion (18), coaxially receiving the laminating mandrel (12) and rotatable about the central axis (B) in relation to the fixed portion (17); the laminating mandrel (12) comprises a central shaft (26, 26' ), a plurality of sectors (30) angularly spaced apart about the central axis (B), and a plurality of linear actuators (31) extending between the central shaft (26, 26' ) and respective sectors (30) to move the sectors (30) themselves between an expanded laminating position and a contracted position; the equipment (10) further comprises first constraining means (35) for connecting in a releasable manner the sectors (30), arranged in the expanded laminating position, to the movable portions (18) of the headers (14, 15), and second constraining means (36) connecting the linear actuators (31) to the sectors (30) in a releasable manner so as to enable the extraction of the central shaft (26, 26' ) and linear actuators (31) from the equipment (10) in the condition in which the sectors (30), in the expanded position, are connected to the movable portions (18) of the headers (14, 15) by means of the first constraining means (35).
B29C 70/32 - 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 sur un moule, un gabarit ou un noyau rotatifs
B29C 33/48 - Moules ou noyaux; Leurs détails ou accessoires comportant des moyens ou conçus spécialement pour faciliter le démoulage d'objets, p.ex. des objets à contre-dépouille avec des moyens rétractables ou démontables
B29D 99/00 - Matière non prévue dans les autres groupes de la présente sous-classe
B64C 1/00 - Fuselages; Caractéristiques structurales communes aux fuselages, voilures, surfaces stabilisatrices ou organes apparentés
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
10.
COHERENT BEAM COMBINATION SYSTEM AND CONTROL METHOD THEREOF
12344) to the phase modulators (42); receive the detection signal (INT) from the optical sensor, indicative of an intensity of the sampled recombined beam; calculate a cost function (J) from the detection signal (INT), wherein the cost function is a function of the intensity of the sampled recombined beam; perform an optimization algorithm of the cost function, configured to maximise the intensity of the sample recombined beam; and provide a plurality of updated phase control signals, based on a result of the optimization algorithm.
H01S 3/10 - 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
H01S 3/13 - Stabilisation de paramètres de sortie de laser, p.ex. fréquence ou amplitude
H01S 3/23 - Agencement de plusieurs lasers non prévu dans les groupes , p.ex. agencement en série de deux milieux actifs séparés
G02B 6/42 - Couplage de guides de lumière avec des éléments opto-électroniques
G02B 27/09 - Mise en forme du faisceau, p.ex. changement de la section transversale, non prévue ailleurs
G02B 27/10 - Systèmes divisant ou combinant des faisceaux
H01S 3/00 - Lasers, c. à d. dispositifs utilisant l'émission stimulée de rayonnement électromagnétique dans la gamme de l’infrarouge, du visible ou de l’ultraviolet
Transmission assembly (3, 3', 3'', 3''' 3'''') for an aircraft (1) capable of hovering, comprising : a first and a second member (7, 8) and support means (9) of the first member (7) with respect to the second member (8); a primary lubrication circuit (20) comprising a primary tank (11) of a lubricating fluid and primary fluidic supply means (12) for supplying fluid to the support means (9); and an emergency lubrication circuit (22) comprising an emergency tank (23) of lubricating fluid fluidically connected to the primary tank (11); and auxiliary fluidic supply means (30) of the lubricating fluid to the support means (9), comprising a nozzle (24); the auxiliary fluidic supply means (30) comprise a dosing device (31, 31', 31'', 31''' 31'''') and a fluidic line (32), which fluidically connects the emergency tank (23) with the dosing device (31, 31', 31'', 31''' 31''''); the dosing device (31, 31', 31", 31''' 31'''') comprising a passage (33, 33'''') for the lubricating fluid from the fluidic line (32) to the nozzle (24), which comprises a plurality of concentrated pressure drop sections (6, 6''''), which are distinct and spaced apart from each other.
A ground station for deliveries and pick-ups by a drone comprising a vertical structure (4) fixable to the ground or to a fixed structure and provided with an arm (5) movable between a rest position and an extended activation position wherein the arm (5) extends transversely in a cantilever fashion from the vertical structure (4); the vertical structure (4) carries a first marker Ml at the top that is designed to be recognised by the drone during flight to activate a step of approach of the drone to the ground station while maintaining a predetermined horizontal distance from the ground station and a first and a second laser emitter (8, 9) defining respectively a first /a second position reference for the drone wherein a portion (3f) of the drone has a first or a second vertical distance DI, D2 from the arm (5) arranged in the extended position; the ground station (2) is configured to carry out a coupling procedure of an end portion (5f) of the arm (5) with a support structure (11) of a load (12) carried by the drone (3).
B64U 10/14 - Plates-formes volantes comportant quatre axes distincts de rotors, p. ex. quadcoptères
A47G 29/14 - Récipients pour déposer des aliments, p.ex. petit déjeuner, lait; Récipients similaires pour colis avec accessoires pour éviter que les articles déposés ne soient indûment retirés
B64C 39/02 - Aéronefs non prévus ailleurs caractérisés par un emploi spécial
B64U 101/60 - Véhicules aériens sans pilote spécialement adaptés à des utilisations ou à des applications spécifiques au transport de marchandises autres que des armes
B64D 1/22 - Enlèvement d'objets à la surface du sol
13.
METHOD FOR ESTIMATING THE ROTOR TORQUES OF AN AIRCRAFT CAPABLE OF HOVERING AND CONTROL UNIT FOR AN AIRCRAFT CAPABLE OF HOVERING
B64C 29/00 - Aéronefs capables d'atterrir ou de décoller à la verticale, p.ex. aéronefs à décollage et atterrissage verticaux [ADAV, en anglais VTOL]
G05B 13/02 - Systèmes de commande adaptatifs, c. à d. systèmes se réglant eux-mêmes automatiquement pour obtenir un rendement optimal suivant un critère prédéterminé électriques
G05D 1/08 - Commande de l'attitude, c. à d. élimination ou réduction des effets du roulis, du tangage ou des embardées
B64D 31/00 - Commande des groupes moteurs; Leur disposition
F02C 7/00 - Caractéristiques, parties constitutives, détails ou accessoires non couverts dans, ou d'un intérêt plus général que, les groupes ; Entrées d'air pour ensembles fonctionnels de propulsion par réaction
14.
METHOD FOR CLASSIFYING THE MANOEUVRES PERFORMED BY AN AIRCRAFT BY SEGMENTATION OF TIME SERIES OF MEASUREMENTS ACQUIRED DURING A FLIGHT OF THE AIRCRAFT
prob prob (NUM_C, W) ) including, for each instant of time of the succession of instants of time, a corresponding probability vector (CX) including, for each class of a plurality of classes of manoeuvres, a corresponding estimate of the probability that, in the instant of time, the aircraft (1) has performed a manoeuvre belonging to the class; and selecting (123), for each instant of time of the succession of instants of time, a corresponding class of manoeuvres, based on the probability estimates of the corresponding probability vector (CX).
G01B 11/16 - Dispositions pour la mesure caractérisées par l'utilisation de techniques optiques pour mesurer la déformation dans un solide, p.ex. indicateur optique de déformation
G01B 11/00 - Dispositions pour la mesure caractérisées par l'utilisation de techniques optiques
G01S 17/66 - Systèmes de poursuite utilisant d'autres ondes électromagnétiques que les ondes radio
G01S 17/14 - Systèmes déterminant les données relatives à la position d'une cible pour mesurer la distance uniquement utilisant la transmission d'ondes à modulation d'impulsion interrompues dans lesquels une impulsion de tension ou de courant est initiée et terminée en fonction respectivement de l'émission d'impulsions et de la réception d'écho, p.ex. en utilisant des compteurs
CONSORZIO NAZIONALE INTERUNIVERSITARIO PER LE TELECOMUNICAZIONI (CNIT) (Italie)
Inventeur(s)
Natali, Federico
De Stefani, Filippo
Acito, Nicola
Corsini, Giovanni
Diani, Marco
Abrégé
iiii). The processor (6) is adapted to normalize (14) the saliency maps (S, Si), resize (15) the normalized saliency maps (SNii Niii ↑) and the normalized saliency map (SNFF) on which to detect the object of interest.
G06V 10/32 - Normalisation des dimensions de la forme
G06V 10/46 - Descripteurs pour la forme, descripteurs liés au contour ou aux points, p.ex. transformation de caractéristiques visuelles invariante à l’échelle [SIFT] ou sacs de mots [BoW]; Caractéristiques régionales saillantes
G06V 10/80 - Fusion, c. à d. combinaison des données de diverses sources au niveau du capteur, du prétraitement, de l’extraction des caractéristiques ou de la classification
G06V 20/52 - Activités de surveillance ou de suivi, p.ex. pour la reconnaissance d’objets suspects
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
G06V 10/75 - Appariement de motifs d’image ou de vidéo; Mesures de proximité dans les espaces de caractéristiques utilisant l’analyse de contexte; Sélection des dictionnaires
18.
RENDERING A SKY VEIL ON AN AVIONIC PRIMARY FLIGHT DISPLAY
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
19.
BIDIRECTIONAL DATA COMMUNICATION SYSTEM, IN PARTICULAR EXPLOITING A CDMA CODING AND TWO UNIDIRECTIONAL DATA BUSES
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.
010121212121010101); a first summing element (23) that sums the first extracted signal and the second extracted signal, thereby generating the first error signal at the first output port; and a second summing element (24) that sums the third extracted signal and the fourth extracted signal, thereby generating the second error signal at the second output port.
CONTROL UNIT AND INDICATOR FOR AN AIRCRAFT CAPABLE OF HOVERING OR FOR A FLIGHT SIMULATION SYSTEM OF SAID AIRCRAFT, AND RELATIVE METHOD FOR ASSISTING THE PERFORMANCE OF A MANOEUVRE
A control unit (46, 46') for an aircraft (1, 1') capable of hovering or for a flight simulation system of the aircraft (1, 1') is described, the control unit (46, 46') is programmed to receive at input at least a first signal associated with real or simulated flight parameters (ALT, OAT; ALT', OAT') of the aircraft (1, 1') and to provide at output a second signal (VNE, VNE') associated with a forward velocity to never exceed of the aircraft (1, 1'); the control unit (46, 46') is programmed to process a third signal (GW, GW') associated with an actual or simulated weight of the aircraft (1, 1'); to associate plurality of tables (T1, T2,.., Tn) to respective intervals (I1, I2,.. Ij) of values of the third signal (GW, GW'); each table (T1, T2,.., Tn) associating a plurality of values of the second signal (VNE, VNE') with a respective first signal (ALT, OAT; ALT', OAT'; AEO, OEI, Power off; AEO', OEI', Power off'); and to process the second signal (VNE, VNE'), based on the table (T1, T2,.., Tn) associated with the relative interval (T1, T2,.. Ij) of the third signal (GW, GW') and the respective first signals (ALT, OAT; ALT', OAT').
B64D 31/00 - Commande des groupes moteurs; Leur disposition
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 19/16 - Conduite des véhicules ou autres moyens de transport
B64D 43/00 - Aménagements ou adaptations des instruments
B64D 45/00 - Indicateurs ou dispositifs de protection d'aéronefs, non prévus ailleurs
B64C 27/00 - Giravions; Rotors propres aux giravions
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
22.
CONTROL UNIT AND INDICATOR FOR AN AIRCRAFT CAPABLE OF HOVERING OR FOR A FLIGHT SIMULATION SYSTEM OF SAID AIRCRAFT, AND RELATIVE METHOD FOR ASSISTING THE PERFORMANCE OF A MANOEUVRE
A control unit (46, 46') for an aircraft (1, 1') capable of hovering or for a flight simulation system of the aircraft (1, 1') is described; the control unit (46, 46') is programmed to: - receive in input a plurality of data associated with equipment (15) and/or kits (25) actually installed or simulated on the aircraft (1, 1') and/or with the operating configuration of the equipment (15) and/or kits (25); the equipment (15) and/or kits (25) causing a reduction of the actual or simulated forward velocity of the aircraft (1, 1'); - store a table (TX) defining a correspondence between each datum and a respective value of a first signal (Vmax, Vmax') associated with a value of maximum forward velocity of the aircraft (1, 1'); and - display the lowest of the first signals (Vmax, Vmax').
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
B64D 43/00 - Aménagements ou adaptations des instruments
G09B 19/16 - Conduite des véhicules ou autres moyens de transport
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
B64C 29/00 - Aéronefs capables d'atterrir ou de décoller à la verticale, p.ex. aéronefs à décollage et atterrissage verticaux [ADAV, en anglais VTOL]
Test device for an aeronautical component ( 2 ) wherein M low- energy impacts are performed on the component to be subjected to testing ( 2 ) by calculating the relative uncertainty Ui of the non-destructive tests. A destructive test (block 120 ) is performed on the aeronautical component ( 2 ) by measuring and storing the value of a quantity VI representative of the elastic stress applied to the component during the destructive test and based on this the uncertainty of the destructive test is calculated (block 130 ). The absolute value of the difference between target values of quantities Ci based on a theoretical model that describes the elastic behaviour of the component to be subjected to testing and the value of the quantity VI representative of the elastic stress applied to the component during the destructive test (ABS ( Ci -Vi ) ) is compared with the product of the uncertainty of the destructive test Al and a scaling factor k in order to certify the theoretical model as describing with sufficient accuracy the behaviour of the aeronautical component during the destructive test.
G01N 3/34 - Recherche des propriétés mécaniques des matériaux solides par application d'une contrainte mécanique en appliquant des efforts répétés ou pulsatoires engendrés par des moyens mécaniques, p.ex. chocs de marteau
24.
CONTROL DEVICE FOR VARYING THE ANGLE OF ATTACK OF THE BLADES OF AN ANTI-TORQUE ROTOR FOR AN AIRCRAFT CAPABLE OF HOVERING
A control device (50) for controlling the variation of the angle of attack of the blades (8) of the anti-torque rotor (4) for an aircraft (1) capable of hovering is described, comprising a control element (16) sliding along a first axis (A) with respect to a shaft (6) of the rotor (4) and rotatable integrally therewith; the control element (16) is operatively connected to a plurality of blades (8) articulated on the shaft (6) in order to vary the angle of attack thereof following a translation of the element (16) itself along the axis (A); a control rod (10) axially sliding along the axis (A) with respect to the shaft (6) and angularly fixed with respect to the axis (A); and a rolling bearing (17) interposed between the control rod (10) and the control element (16), sliding along the axis (A) with respect to the shaft (6) and integrally with the control rod (10); the control device (50) comprises a threaded element (51) screwed onto the control rod (10) and cooperating with the bearing (17) to constrain it axially with respect to the control rod (10) and a bushing (52) coupled in an angularly and axially fixed manner to the threaded element (51), and in an angularly fixed manner to the control rod (10).
B64C 27/78 - Mécanismes pour la commande du réglage ou du mouvement de la pale par rapport à la tête du rotor, p.ex. mouvement de traînée en conjonction avec le réglage du pas des pales du rotor anticouple
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
F16B 37/14 - Ecrous-chapeaux; Chapeaux d'écrous ou de boulons
F16B 39/08 - Blocage des vis, boulons ou écrous dans lequel le verrouillage s'effectue après vissage avec un chapeau agissant contre l'écrou relié au boulon par une broche ou une goupille fendue
25.
METHOD AND SYSTEM FOR DETECTING FLIGHT REGIMES OF AN AIRCRAFT, ON THE BASIS OF MEASUREMENTS ACQUIRED DURING AN AIRCRAFT FLIGHT
1NQ1NQik,iφkφk (t) ), the smoothed series of samples forming a smoothed unknown matrix (TFDMx' ); on the basis of the base functions, applying (206) to the smoothed unknown matrix and to the corresponding sets of coefficients a classifier trained to generate, for each flight regime among a plurality of flight regimes, a corresponding estimate of the probability that the smoothed unknown matrix and the corresponding sets of coefficients belong to a cluster relative to the flight regime; identifying (208) a flight regime in which the aircraft operated, on the basis of the estimates generated by the classifier.
A method of joining a first element (2) in composite material with a second element (3) in composite material to define a structural component (4) of an aircraft is described, the method comprises the steps of: a) arranging the first element (2) in contact on the second element (3); b) applying a non-rigid heating layer (6) on the first element (2); c) applying a layer of shape memory thermoplastic polymer ( 7 ), pre-loaded in a compressed non-equilibrium condition, onto the heating layer (6); d) applying a vacuum bag (8) to the assembly thus obtained; e) sealing the vacuum bag (8) to define a vacuum chamber (10) housing the first element (2), at least part of the second element (3), the heating layer (6) and the shape memory layer (7); f) applying vacuum inside the vacuum chamber (10); g) applying heat to the first element (2), to the second element (3) and to the shape memory layer (7) by activating the heating layer (6); h) expanding the shape memory layer (7) from the compressed non- equilibrium condition to an expanded equilibrium condition by means of the step g) of applying heat; 1) applying pressure to the first element (2) for compacting it against the second element (3) by means of the step h) of expanding.
B29C 65/18 - Assemblage d'éléments préformés; Appareils à cet effet par chauffage, avec ou sans pressage avec un outil chauffé
B29C 65/50 - Assemblage d'éléments préformés; Appareils à cet effet en utilisant des adhésifs utilisant des rubans adhésifs
B29C 73/12 - Appareils à cet effet, p.ex. pour les poser
B29C 73/32 - Appareils ou accessoires non prévus ailleurs pour presser localement ou pour chauffer localement utilisant un élément élastique, p.ex. un sac gonflable
B29L 31/30 - Véhicules, p.ex. bateaux ou avions, ou éléments de leur carrosserie
An aircraft window configured to reduce the intensity of vibrations transmitted from outside the aircraft to inside the aircraft cabin comprising: a first element of transparent material (2) arranged, in use, facing the outside of the aircraft; a second element of transparent material (3) arranged, in use, facing the cabin; a gap (4) that separates the first and second elements of transparent material (2,3) which are arranged facing and spaced apart from one another, a first transparent sheet element (5) applied to a first face of the first element (2) facing the gap; and at least one second transparent sheet element (7) applied to a second face of the second element (3) facing the gap. The first and second transparent sheet elements (5,7) are made of transparent viscoelastic material.
Aircraft (1) comprising: a moving system (10) adapted for use when the aircraft (1) is in flight to move sensing means (18) of the aircraft between a rest position, wherein the sensing means (18) are arranged within the aircraft, and a work position, wherein the sensing means (18) face directly, along a sensing direction (y), toward the outside of the aircraft (1) and towards the ground when the aircraft (1) is in flight, comprising: a frame (12) arranged inside the aircraft (1); a slide (14), to support said sensing means (18); and a pair of guides (16), each comprising a rail part (16a), supported on said frame (12), and at least one draw part (16b; 16b') arranged telescopically slidable relative to the relevant rail part (16a) along a direction of movement (x) that is essentially perpendicular to said sensing direction (y); the slide (14) being mounted integrally with the draw parts (16b; 16b') of the pair of guides (16) in such a way to slide along the direction of movement (x) internally within the aircraft (1) to move said sensing means (18) between said rest position and said work position.
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).
The present invention relates to a system for generating light radiation to neutralize microorganisms. Said system comprises a light source (1 ) for emitting a light radiation, storage means (2) with one or more unique identification codes, each of which is associated with a respective microorganism, and at least one respective wavelength range associated with said microorganism, and a logic control unit (3). Said logic control unit (3) is configured to: o select a wavelength range based on the microorganism to be neutralized, o activate said light source (1) in such a way that the light radiation emitted by said light source (1) has a wavelength within said selected wavelength range, so that, when the system is in use, said light radiation induces an optical resonance in the microorganism, causing a denaturation of the genetic patrimony of said microorganism.
A61L 2/10 - Procédés ou appareils de désinfection ou de stérilisation de matériaux ou d'objets autres que les denrées alimentaires ou les lentilles de contact; Accessoires à cet effet utilisant des phénomènes physiques des radiations des ultraviolets
A61L 2/24 - Appareils utilisant des opérations programmées ou automatiques
A61M 1/14 - Systèmes de dialyse; Reins artificiels; Oxygénateurs du sang
A61L 2/00 - Procédés ou appareils de désinfection ou de stérilisation de matériaux ou d'objets autres que les denrées alimentaires ou les lentilles de contact; Accessoires à cet effet
A61L 2/08 - Procédés ou appareils de désinfection ou de stérilisation de matériaux ou d'objets autres que les denrées alimentaires ou les lentilles de contact; Accessoires à cet effet utilisant des phénomènes physiques des radiations
A61B 1/267 - Instruments pour procéder à l'examen médical de l'intérieur des cavités ou des conduits du corps par inspection visuelle ou photographique, p.ex. endoscopes; Dispositions pour l'éclairage dans ces instruments pour les voies respiratoires, p.ex. laryngoscopes, bronchoscopes
A61B 1/06 - Instruments pour procéder à l'examen médical de l'intérieur des cavités ou des conduits du corps par inspection visuelle ou photographique, p.ex. endoscopes; Dispositions pour l'éclairage dans ces instruments avec dispositifs d'éclairement
A61B 1/273 - Instruments pour procéder à l'examen médical de l'intérieur des cavités ou des conduits du corps par inspection visuelle ou photographique, p.ex. endoscopes; Dispositions pour l'éclairage dans ces instruments pour l'appareil digestif supérieur, p.ex. œsophagoscopes, gastroscopes
A61B 5/00 - Mesure servant à établir un diagnostic ; Identification des individus
32.
METHOD FOR MANUFACTURING A CORE FOR A SOUND-ABSORBING PANEL WITH SANDWICH STRUCTURE FOR NOISE REDUCTION IN AN AIRCRAFT
A method for manufacturing a core (10) for a panel (100) for an aircraft comprises the steps of: arranging first sheet-shaped partitioning elements (12), each having a plurality of vertical slits (16) extending transversely from a first edge thereof (12a), spaced from each other so that the distance between two successive first partitioning elements (12) is not constant; arranging second sheet- shaped partitioning elements (14), each with a plurality of vertical slits (16), extending transversely from one of its first edges (14a), on the first partitioning elements (12), transversely thereto, so that each vertical slit (16) of the second partitioning elements (14) interlocks with a respective vertical slit (16) of a respective first partitioning element (12), to define a plurality of cells (26) delimited laterally by a pair of opposing first partitioning elements (12) and a pair of opposing second partitioning elements (14).
F02C 7/045 - Entrées d'air pour ensembles fonctionnels de turbines à gaz ou de propulsion par réaction comportant des dispositifs destinés à supprimer le bruit
F02K 1/44 - Tuyères comportant des moyens, p.ex. un écran, réduisant la propagation sonore dans une direction déterminée
F02K 1/82 - Parois des tubulures de jet, p.ex. chemises
B64C 1/40 - Insonorisation ou isolation calorifique
33.
METHOD FOR MANUFACTURING A CORE FOR A SOUND-ABSORBING PANEL WITH SANDWICH STRUCTURE FOR NOISE REDUCTION IN AN AIRCRAFT
Method for manufacturing a core (10) for an aircraft panel (100) with the steps of: arranging first sheet-shaped partitioning elements (12), each with vertical slits (16), extending transversely from a first edge (12a), and transverse slits (22) extending transversely to the vertical slits (16), spaced from each other; arranging second sheet-shaped partitioning elements (14), each with vertical slits (16) extending transversely from a first edge (14a), on the first partitioning elements (12), transversely thereto, so that each vertical slit (16) of the second partitioning elements (14) interlocks with a respective vertical slit (16) of a respective first partitioning element (12), so that the first partitioning elements (12) and the second partitioning elements (14) define a plurality of cells (26); and arranging horizontal partitioning elements (24), through a pair of transverse slits (22) of a respective pair of successive first partitioning elements (12).
F02C 7/045 - Entrées d'air pour ensembles fonctionnels de turbines à gaz ou de propulsion par réaction comportant des dispositifs destinés à supprimer le bruit
F02K 1/44 - Tuyères comportant des moyens, p.ex. un écran, réduisant la propagation sonore dans une direction déterminée
F02K 1/82 - Parois des tubulures de jet, p.ex. chemises
B64C 1/40 - Insonorisation ou isolation calorifique
34.
METHOD FOR MANUFACTURING A CORE FOR A SOUND-ABSORBING PANEL WITH SANDWICH STRUCTURE FOR NOISE REDUCTION IN AN AIRCRAFT
A method for manufacturing a core (10) for a panel (100) for an aircraft comprises the steps of: arranging a plurality of first sheet- shaped partitioning elements (12), each having a plurality of vertical slits (16) extending transversely from a first edge thereof (12a), wherein the distance between two successive vertical slits (16) is not constant, spaced from each other; arranging a plurality of second sheet-shaped partitioning elements (14), each with a plurality of vertical slits (16), extending transversely from one of its first edges (14a), transversely on the first partitioning elements (12) so that each vertical slit (16) of the second partitioning elements (14) interlocks with a respective vertical slit (16) of a respective first partitioning element (12), to define a plurality of cells (26), each delimited laterally by a pair of opposing first partitioning elements (12) and a pair of opposing second partitioning elements (14).
F02C 7/045 - Entrées d'air pour ensembles fonctionnels de turbines à gaz ou de propulsion par réaction comportant des dispositifs destinés à supprimer le bruit
F02K 1/44 - Tuyères comportant des moyens, p.ex. un écran, réduisant la propagation sonore dans une direction déterminée
F02K 1/82 - Parois des tubulures de jet, p.ex. chemises
B64C 1/40 - Insonorisation ou isolation calorifique
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
B64C 29/00 - Aéronefs capables d'atterrir ou de décoller à la verticale, p.ex. aéronefs à décollage et atterrissage verticaux [ADAV, en anglais VTOL]
36.
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).
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).
Method for recovering the digital error of a digital array antenna after powering it off/on again, the antenna (1) having a plurality of radiating elements (2), respective transmitting/receiving modules (3) operating at certain radio frequencies and a non- volatile memory (6), wherein at the end of a calibration of the antenna (1), for each radio frequency and each radiating element (2), a first and a second digital state (SCalRx, SCalTx) are acquired and recorded in the non-volatile memory (6) which are relative to the radio frequency in reception and, respectively, in transmission after powering the antenna (1) off and on again, for each radiating element (2), a third and a fourth digital state (SCurRx, SCurTx) are acquired which are relative to a certain test radio frequency in reception and, respectively, in transmission; for each radiating element (2), the third digital state (SCurRx) is compared with the first digital state (SCalRx) at the test radio frequency to determine first compensation coefficients (AtRx, AcpRx) and the fourth digital state (SCurTx) is compared with the second digital state (SCalTx) at the test radio frequency to determine second compensation coefficients (AtTx, ΔφΤx); the relative first compensation coefficients (AtRx, AφRx) in reception and the relative second compensation coefficients (ΔtΤx, ΔφΤx) in transmission are applied to each transmitting/receiving module (3).
G01S 7/35 - DÉTERMINATION DE LA DIRECTION PAR RADIO; RADIO-NAVIGATION; DÉTERMINATION DE LA DISTANCE OU DE LA VITESSE EN UTILISANT DES ONDES RADIO; LOCALISATION OU DÉTECTION DE LA PRÉSENCE EN UTILISANT LA RÉFLEXION OU LA RERADIATION D'ONDES RADIO; DISPOSITIONS ANALOGUES UTILISANT D'AUTRES ONDES - Détails des systèmes correspondant aux groupes , , de systèmes selon le groupe - Détails de systèmes non impulsionnels
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).
krfrii), as a function of the duration of the respective representative flight; and determining (250) a state of use of the group of aircraft, starting from the load sequence.
11wiiw1,11,181,18). The method includes detecting (800, 802,804, 806) anomalies of the transmission system (1) on the basis of the groups of synthetic indexes.
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
G06F 3/03 - Dispositions pour convertir sous forme codée la position ou le déplacement d'un élément
43.
TEST TOOL FOR CHECKING THE PROFILE OF A STRUCTURAL COMPONENT AND METHOD FOR TESTING THE CONFORMITY OF A PROFILE OF A STRUCTURAL COMPONENT TO A SPECIFIC TOLERANCE
A test tool (1) for checking the profile of a structural component (2) is described, the tool (1) comprising a base (3) defining a support surface (4) for the structural component (2) and a plurality of force application devices (6) arranged in respective distinct positions along the base (3) at a predetermined distance from one another and each configured to apply, at the respective position, a control force to the structural component (2) supported by the base (3); wherein each force application device (6) comprises an actuation member (10) and a tip (11), and arrangeable, by means of the actuation member (10), between: an open position, in which the tip (11) is at a non-zero distance from the support surface (4) and from the structural component (2) resting on it, in use; and a closed position, in which the tip (11) is pressed against said structural component (2) to apply said control force thereon and thus push it completely against the support surface (4) to check the conformity of said profile to a specific tolerance; and wherein each force application device (6) further comprises: a spring member (14) operatively coupled to the tip (11) and compressible by means of said pressing of the tip (11) against the structural component (2); and an indicator element (15) carried by the spring member (14), having an external surface (16) with at least one distinctive surface feature (17) and movable by compression of the spring member (14) to render the distinctive surface feature (17) detectable or undetectable according to the extent of the control force applied, in use, to the structural component (2) by means of said pressing of the tip (11).
G01L 1/04 - Mesure des forces ou des contraintes, en général en mesurant la déformation élastique de jauges, p.ex. de ressorts
B25B 5/12 - Dispositions pour transmettre le mouvement aux mâchoires utilisant des leviers articulés
F16B 31/02 - Assemblages à vis spécialement modifiés en vue de résister à une charge de traction; Boulons de rupture signalant ou limitant la charge de traction
G01L 5/00 - Appareils ou procédés pour la mesure des forces, du travail, de la puissance mécanique ou du couple, spécialement adaptés à des fins spécifiques
G01M 5/00 - Examen de l'élasticité des structures ou ouvrages, p.ex. fléchissement de ponts ou d'ailes d'avions
44.
ASSEMBLY FOR MOUNTING AN UNDERWING PYLON TO A RIB OF AN AIRCRAFT WING
An assembly for removably mounting an underwing pylon (11) to a rib (10) of an aircraft wing is described. The assembly comprises a prismatic body (12) insertable into a prismatic cavity (22) of the pylon, a threaded retaining element (14) having an upwardly tapered outer conical surface (15), and a vertical threaded pin (13) inserted through a vertical through hole (12e) of the prismatic body (12). The assembly further comprises an anti-rotation device (31, 32) for rotationally locking the threaded retaining element (14) to the prismatic body (12) relative to a vertical axis (A).
B64D 7/04 - 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 fixes
B64D 27/18 - Aéronefs caractérisés par le type ou la position des groupes moteurs du type à réaction à l'intérieur de la voilure ou fixés à celle-ci
45.
PLANETARY GEAR FOR A TRANSMISSION FOR AN AIRCRAFT CAPABLE OF HOVERING
A description is provided of a planetary gear (21; 21'') comprising a sun (15) rotatable around a first axis (B), a crown (17) angularly fixed with respect to the first axis (B); two satellites (19) that are meshing, rotatable around respective second axes (I); a satellite carrier (30) rotatable around the first axis (B) and comprising at least two first pins (32) with respect to which the satellites (19) are rotatable around respective second axes (I); and a plurality of bearings (40) comprising: a first ring (41) defining a first raceway (42) that is at least partially spherical; a second ring (43; 43'') defining a second raceway (44); and a plurality of rolling bodies (45; 46) shaped as an hourglass rolling on the first spherical raceway (42) and a second raceway (44); each rolling body (45; 46) being in contact with the raceways (42, 44) at a line (L1; L3, L2, L4) with axial ends (61; 63, 62; 64) lying on respective straight lines (R1; R3, R2; R4) tilted between them and converging in a point (S1; S2) lying on a median plane (P1; P2) of the rolling body (45; 46) and on the second axis (I); the straight lines (R1, R3; R2, R4) define a first angle (α1; α2), whose bisector (T1; T2) lies on the first median (P1; P2).
F16C 19/38 - Paliers à contact de roulement pour mouvement de rotation exclusivement avec roulements à rouleaux essentiellement du même gabarit, disposés dans une ou plusieurs rangées circulaires, p.ex. roulements à aiguilles pour charges à la fois axiales et radiales avec plusieurs rangées de rouleaux
F16C 23/08 - Roulements à billes ou à rouleaux à autoréglage
F16C 33/30 - Eléments de roulements à billes ou à rouleaux
F16C 33/36 - Rouleaux; Aiguilles avec gorges pratiquées dans les surfaces portantes
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
nnn), and each being glued to both the support structure (12) and a respective n-th damping mass (14) in order to support said particular n-th damping mass on the support structure (12) so that the former is free to vibrate relative to the latter; wherein, for each n from 2 to N, each n-th damping mass (14) is arranged to at least partially surround an n-l-th damping mass (14); and wherein the first damping mass (14) has a solid semi-cylindrical shape, and the remaining damping masses (14) have a hollow semi-cylindrical shape.
F16F 7/108 - Amortisseurs de vibrations; Amortisseurs de chocs utilisant un effet d'inertie l'élément d'inertie étant monté de manière élastique sur des ressorts en matière plastique
B64C 1/40 - Insonorisation ou isolation calorifique
An aircraft (1) capable of hovering is described, comprising a motor member (10); a rotor (5) connected to the motor member (10); a transmission shaft (11) rotatable around a first axis (B) and adapted to drive the rotor (5); and a transmission (9) interposed between the motor member (10) and the rotor (5) and comprising a planetary gear (21) formed by a sun (7) rotatable around a second axis (D); a crown (17) that is angularly fixed; and two satellites (19) meshing, each, with the crown (17) and the sun (15), and rotatable around respective third axes (I), which are, in turn, rotatable around the second axis (D); and a satellite carrier (30) rotatable around the second axis (D) and comprising two first pins (32) with respect to which the satellites (19) are rotatable around the respective third axes (E); the transmission (9) comprises an interface (50), angularly integral with the satellite carrier (30) around the second axis (D) and said transmission shaft (11) around the first axis (B); the interface (50) being coupled to said satellite carriers (30) and the transmission shaft (11) so as to allow an angular misalignment between the second axis (B) and a portion (55) of the interface (50).
F02C 7/36 - Transmission de puissance entre les différents arbres de l'ensemble fonctionnel de turbine à gaz, ou entre ce dernier et l'utilisateur de puissance
F16H 1/28 - Transmissions à engrenages pour transmettre un mouvement rotatif avec engrenages à mouvement orbital
F16H 1/48 - Moyens particuliers pour compenser le défaut d'alignement des axes
F16H 57/08 - TRANSMISSIONS - Parties constitutives générales des transmissions des transmissions à organes à mouvement orbital
49.
ANTI-ICING DEVICE FOR INTAKE OPENING OF THE ENGINE NACELLE FOR TURBOJET OR TURBOFAN ENGINES
An anti-icing device (1) for intake opening (2) of the engine nacelle (3) comprising: a first Joule effect heater device (10) coupled to a first outer annular wall (5) of a front annular portion (4) of the nacelle and powered by electrical energy present on the aircraft; a second Joule effect heater device (11) coupled to a second inner annular wall (6) of the front annular portion (4), powered by electric energy present on the aircraft and configured, when powered, to heat the outer surface of the second inner wall (6) so that any ice formed on the second inner annular wall (6) is transformed into a film of water moving along the second annular wall (6) towards a sound-absorbing tubular wall (8); and a discontinuity element (12) provided between the second inner annular wall (6) and the sound-absorbing tubular wall (8) and configured to perform the detachment of the liquid film (F) flowing on the inner annular wall (6) due to the kinetic speed of the airflow sucked by the engine directing the nebulized water particles (G) towards the engine itself.
The system comprises a main structure (12) in which a firing chamber (14) and a braking and recovery tank (16), adjacent to the firing chamber (14), are positioned. The firing chamber (14) is intended for housing a firearm (18) configured for firing at least one projectile (P) into the braking and recovery tank (16). Furthermore, the braking tank (16) is configured for containing a liquid capable of braking the projectile (P) coming from the firing chamber (14) and fired by the firearm (18). Furthermore, the braking and recovery tank (16) has an opening (22) in front of which a barrel (20) of the firearm (18) is to be positioned. The opening (22) is configured to allow the projectile (P) to gain access to the braking and recovery tank (16) when the projectile (P) is fired by the firearm (18). There is also a counter barrel assembly (24) placed between the firing chamber (14) and the braking and recovery tank (16), and configured for receiving and guiding through itself the projectile (P) fired by the firearm (18), so as to cause the projectile (P) to enter the braking and recovery tank (16).
The system (10) comprises a main structure (12) in which a firing chamber (14) and a braking and recovery tank (16), adjacent to the firing chamber (14), are positioned. The firing chamber (14) is intended for housing a firearm (18) configured for firing a projectile (P) into the braking and recovery tank (16). Furthermore, the braking and recovery tank (16) is configured for containing a liquid capable of braking the projectiles (P) coming from the firing chamber (14) and fired by the firearm (18). There is a collecting assembly (36) placed in the braking and recovery tank (16) and configured for recovering the braked projectiles (P) that have fallen to the bottom of the braking and recovery tank (16). The collecting assembly (36) comprises a basket (38) configured for receiving and collecting the fallen pro j ectiles (P), and a pushing device (42) configured for pushing the fallen projectiles (P) towards the basket (38).
The system (10) comprises a main structure (12) in which a firing chamber (14) and a braking and recovery tank (16), adjacent to the firing chamber (14), are positioned. The firing chamber (14) is intended for housing a firearm (18) configured for firing a projectile (P) into the braking and recovery tank (16). Furthermore, the braking tank (16) is configured for containing a liquid capable of braking the projectile (P) coming from the firing chamber (14) and fired by the firearm (18). There is also a covering panel (48) configured for removably and reversibly closing the open top of the firing chamber (14).
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 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.
B64F 5/10 - Fabrication ou assemblage d’aéronefs, p.ex. gabarits à cet effet
B64G 1/22 - Parties de véhicules spatiaux ou équipements spécialement destinés à être fixés dans ou sur ces véhicules
B32B 37/10 - Procédés ou dispositifs pour la stratification, p.ex. par polymérisation ou par liaison à l'aide d'ultrasons caractérisés par la technique de pressage, p.ex. faisant usage de l'action directe du vide ou d'un fluide sous pression
55.
INDICATOR FOR AN AIRCRAFT CAPABLE OF HOVERING AND METHOD FOR ASSISTING PERFORMING A MANOEUVRE FOR THE AFORESAID AIRCRAFT
It is disclosed an indicator (16a) for an aircraft (1) capable of hovering, comprising a first indication (35) associated to the value of vertical speed of the aircraft (1) itself; the indicator (16a) comprises a first area (100) wherein a second indication (102) can be displayed that is associated to a Vortex Ring State condition being reached.
B64C 27/00 - Giravions; Rotors propres aux giravions
B64C 29/00 - Aéronefs capables d'atterrir ou de décoller à la verticale, p.ex. aéronefs à décollage et atterrissage verticaux [ADAV, en anglais VTOL]
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
56.
"METHOD AND SYSTEM FOR DETECTING AND CLASSIFYING MANOEUVRES EXECUTED BY AN AIRCRAFT ON THE BASIS OF MEASURES ACQUIRED DURING A FLIGHT OF THE AIRCRAFT
pkpkpkkkkkkkkk) an output classifier (151;251;561;721) to generate estimates indicative of the probability that the aircraft (3) was performing manoeuvres belonging to the macrocategories (MC).
A microphone calibration method, in particular a microphone for aeronautical use, comprising the following steps, coupling a reference microphone (3) to a first end (2-a) of a first standing-wave tube (2); coupling a microphone subjected to calibration (5) to a first end (4-a) of a second standing-wave tube (4); supplying an acoustic input signal to the second end of the first and second tubes so that plane standing-waves propagate in the tubes; measuring the sound pressure of the acoustic signal detected by the first and second microphones (3, 5); increasing the sound pressure of the acoustic input signal from an initial value until a first sound pressure value DB1r is measured by means of the reference microphone (3) and simultaneously detecting a first sound pressure value DB1t by means of the microphone subjected to calibration (5); further increasing the sound pressure of the acoustic input signal by a first amount ΔDΒ1 and detecting a second sound pressure value DB2r by means of the reference microphone (3) and simultaneously detecting a second sound pressure value DB2t by means of the microphone subjected to calibration; decreasing the sound pressure of the acoustic input signal by a second amount -ΔDΒ2 greater than the first amount ΔDΒ1 and detecting a third sound pressure value DB3r by means of the reference microphone (3) and simultaneously detecting a third sound pressure value DB3t by means of the microphone subjected to calibration (5); again, increasing the sound pressure of the acoustic input signal by a third amount ΔDΒ3 and detecting a fourth sound pressure value by means of the reference microphone (3) and simultaneously detecting a fourth sound pressure value with the microphone subjected to calibration (5); the sum of the first and third amounts corresponding to the absolute value of the second amount; controlling whether the fourth sound pressure value detected by means of the microphone subjected to calibration substantially corresponds to the first sound pressure value DB1t by means of the same microphone subjected to calibration and in the case of a positive outcome detecting a correct calibration of the microphone.
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 70/46 - 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 70/44 - 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 70/54 - 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
B64C 1/00 - Fuselages; Caractéristiques structurales communes aux fuselages, voilures, surfaces stabilisatrices ou organes apparentés
59.
SYSTEM FOR PERFORMING SHOCK TESTS, IN PARTICULAR UNDER HIGH ACCELERATION
The system (10) and the method envisage the use of a carrier (12) intended to house an assembly (14) to be subjected to a shock test. The carrier (12) is a container or casing which is reclosable after having inserted the assembly (14) therein. There is a tubular guide (16) having a pair of ends (18, 20) and defining an inner cavity (22) through which the carrier (12) is movable, in a guided manner, between such ends (18, 20). A thrust tank (24) contains a pressurized fluid and is connected to the inner cavity (22) in proximity to one end (18) of the tubular guide (16) and in a position upstream of the carrier (12). The pressurized fluid can thrust the carrier (12) through the inner cavity (22) towards the other end (20) of the tubular guide (16), subjecting the carrier (12) to a thrust acceleration suitable for simulating the effects of a shock undergone by the assembly (14).
A method for the integration of continuous J shaped spars in extended panels of composite material in which J shaped spars are each arranged on a rectilinear support (25) having at least one right triangle shaped portion, and the spars carried by the respective rectilinear supports (25) are subsequently arranged on a stratified structure (4) carried by a mould (1). A vacuum bag (42) is created which covers the stratified structure (4), the rectilinear supports (25), and the J shaped spars. Holes (F) are created in the vacuum bag at respective connection points (50) made along each rectilinear support (25). A supporting structure (30) provided with hooking and adjusting elements (31) with the connection points (50) adjusts the position of each hooking and adjusting element (31) with respect to the supporting structure (30) in order to position the rectilinear support (25) in a direction parallel to the vertical so that the position of the end portion (12) of the J shaped spar, with respect to the mould, corresponds to that foreseen by the design.
B29C 65/00 - Assemblage d'éléments préformés; Appareils à cet effet
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 65/48 - Assemblage d'éléments préformés; Appareils à cet effet en utilisant des adhésifs
B29C 65/78 - Moyens pour la manipulation des éléments à assembler, p.ex. pour la fabrication de récipients ou d'objets creux
B29L 31/30 - Véhicules, p.ex. bateaux ou avions, ou éléments de leur carrosserie
B29K 105/24 - Présentation, forme ou état de la matière moulée réticulée ou vulcanisée
61.
INNOVATIVE THREE-DIMENSIONAL U-SHAPED ARCHITECTURE FOR TRANSMIT/RECEIVE MODULES OF AESA SYSTEMS
NN/2NN/2NN/2N/2NN respective transmission and/or reception front-end modules (59, 6) and configured to carry out beam steering functions including signal phase-shifting, and attenuation and/or amplification functions.
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
H01Q 3/26 - Dispositifs pour changer ou faire varier l'orientation ou la forme du diagramme de directivité des ondes rayonnées par une antenne ou un système d'antenne faisant varier la distribution de l’énergie à travers une ouverture rayonnante
H01Q 1/02 - Dispositifs de dégivrage; Dispositifs de séchage
The method for manufacturing a panel (10) for aircraft comprises the steps of: arranging, on a curing surface (22), a skin (12) of pre-preg composite material; arranging a plurality of pre-formed, uncured composite stringers (14), each having an open cross section with a web (16) and a base (18) transverse to each other so that a first base portion (18a) protrudes toward a first side (SX) and a second base portion (18b) protrudes toward a second side (DX); arranging said plurality of stringers (14) on the skin (12) with the base (18) in contact with the skin (12); arranging, on each stringer (14), a respective first mandrel (M1) so as to completely cover said first base portion (18a) and a respective second mandrel (M2) so as to completely cover said second base portion (18b); and having the skin (12) and the plurality of stringers (14) undergo a co-curing process in autoclave with vacuum bag.
B64C 3/24 - Structures moulées ou venues de fonderie
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"
The present invention relates to a product comprising a substrate (9) and a multilayer coating (1) for the thermal control of a surface (6) comprising a first inner layer (2) intended to be deposited on said surface, a second intermediate layer (3) applied on said first inner layer (2) and a third outer layer (4) applied on said second intermediate layer (3) in which: said first inner layer (2) comprises a co-dispersion of conductive nanoparticles and dielectric nanoparticles, wherein the volume fraction of conductive nanoparticles increases along the thickness of said first inner layer moving away from said second intermediate layer (3); said second intermediate layer comprises a plurality of layers wherein at least one layer of a dielectric material transparent in the visible with a high refractive index in the visible (3') is alternated with at least one layer of a dielectric material transparent in the visible with a low7 refractive index in the visible (3') and wherein the refractive index of each layer of dielectric material transparent in the visible with high refractive index in the visible (3') is higher than the refractive index of each adjacent layer of dielectric material transparent in the visible with low refractive index in the visible (3') and said third outer layer (4) made of a conductive oxide transparent in the visible having a resistivity of less than 1x10-3 ohm x cm. There is also provided an optical solar reflector comprising the product.
G02B 1/16 - Revêtements optiques obtenus par application sur les éléments optiques ou par traitement de la surface de ceux-ci ayant un effet antistatique, p.ex. revêtements conducteurs électriques
B82Y 20/00 - Nano-optique, p.ex. optique quantique ou cristaux photoniques
H01L 31/054 - Dispositifs à semi-conducteurs sensibles aux rayons infrarouges, à la lumière, au rayonnement électromagnétique d'ondes plus courtes, ou au rayonnement corpusculaire, et spécialement adaptés, soit comme convertisseurs de l'énergie dudit rayonnement e; Procédés ou appareils spécialement adaptés à la fabrication ou au traitement de ces dispositifs ou de leurs parties constitutives; Leurs détails adaptés comme dispositifs de conversion photovoltaïque [PV] Éléments optiques directement associés ou intégrés à la cellule PV, p.ex. moyens réflecteurs ou concentrateurs de lumière
F24S 23/70 - Agencements pour concentrer les rayons solaires pour les collecteurs de chaleur solaire avec des réflecteurs
An isostatic mounting system (1) is described to support a sensor (2) and to minimise the thermal conductivity between the sensor (2) and a carrier thereof. An isostatic mounting system (1) comprises at least one support foot (6) configured to be fixed, in use, to a structure (4) of the carrier, and at least one leg (7) extending from the support foot (6). The support foot (6) is.made of a full solid material and the leg (7) has a lattice structure (11) made of the same material of the support foot (6).
F16M 11/22 - Infrastructure avec ou sans roues à hauteur sensiblement constante, p.ex. avec colonne ou pieds de longueur constante
F16M 13/02 - Autres supports ou appuis pour positionner les appareils ou les objets; Moyens pour maintenir en position les appareils ou objets tenus à la main pour être portés par un autre objet ou lui être fixé, p.ex. à un arbre, une grille, un châssis de fenêtre, une bicyclette
B22F 10/00 - Fabrication additive de pièces ou d’objets à partir de poudres métalliques
65.
METHOD FOR CONTROLLING AN AIRCRAFT CAPABLE OF HOVERING AND RELATIVE AIRCRAFT
A method for controlling an aircraft (1) capable of hovering is described, comprising a first engine (10a); a second engine (10b); at least one rotor (3); and a transmission (8) interposed between the first and second engine (10a, 10b) and the rotor (3); the transmission (8) comprises a first and a second inlet (12a, 12b) connected respectively to a first outlet member (11a) of the first engine (10a) and to a second outlet member (11b) of the second engine (10b); the method comprises step i) of placing the aircraft (1) in a first configuration, in which the first and second engine (10a, 10b) make available a first and a second power value (PI, P2); or in a second configuration, in which the first engine (10a) makes available a third power value (P3) greater than the first power value (P1) to the first inlet (12a), and the second engine (10b) delivers a nil power value (P4) to the second inlet (12b); the method also comprises, characterised in that it comprises the steps of ii) detecting a series of parameters associated with the operating conditions of the aircraft (1); and iii) enabling the transition of the aircraft (1) from the first configuration to the second configuration, when the parameters assume respective first values.
F02C 7/36 - Transmission de puissance entre les différents arbres de l'ensemble fonctionnel de turbine à gaz, ou entre ce dernier et l'utilisateur de puissance
F02C 3/113 - Ensembles fonctionnels de turbines à gaz caractérisés par l'utilisation de produits de combustion comme fluide de travail ayant une turbine entraînant un compresseur avec plusieurs rotors raccordés par transmission de puissance aves des transmissions de puissance variables entre les rotors
F02C 6/02 - Ensembles fonctionnels multiples de turbines à gaz comportant une sortie de puissance commune
66.
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"") 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.
B64C 3/24 - Structures moulées ou venues de fonderie
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 70/88 - 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
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
B29D 99/00 - Matière non prévue dans les autres groupes de la présente sous-classe
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 5/14 - Produits stratifiés caractérisés par l'hétérogénéité ou la structure physique d'une des couches caractérisés par une couche différant en certains endroits du fait de sa constitution ou de sa structure physique, p.ex. plus dense superficiellement
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
B32B 33/00 - Produits stratifiés caractérisés par des propriétés particulières ou des caractéristiques de surface particulières, p.ex. par des revêtements de surface particuliers; Produits stratifiés conçus pour des buts particuliers non couverts par une seule autre classe
B32B 38/00 - Opérations auxiliaires liées aux procédés de stratification
B64C 1/00 - Fuselages; Caractéristiques structurales communes aux fuselages, voilures, surfaces stabilisatrices ou organes apparentés
67.
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).
B64C 3/24 - Structures moulées ou venues de fonderie
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 70/88 - 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
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
B29D 99/00 - Matière non prévue dans les autres groupes de la présente sous-classe
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 5/14 - Produits stratifiés caractérisés par l'hétérogénéité ou la structure physique d'une des couches caractérisés par une couche différant en certains endroits du fait de sa constitution ou de sa structure physique, p.ex. plus dense superficiellement
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
B32B 33/00 - Produits stratifiés caractérisés par des propriétés particulières ou des caractéristiques de surface particulières, p.ex. par des revêtements de surface particuliers; Produits stratifiés conçus pour des buts particuliers non couverts par une seule autre classe
B32B 38/00 - Opérations auxiliaires liées aux procédés de stratification
68.
AUXILIARY DEVICE FOR GUIDING A DRILL AND FOR SUCTIONING DUST AND SCRAPS
The invention relates to an auxiliary device (10) for guiding a portable rotary drill (A) and for the suction of dust and scraps generated by drilling or countersinking operations performed by the drill (A); the auxiliary device (10) comprises: a first and a second operating unit (11, 12), which are configured to be arranged on opposite sides of an element (D) or of a plurality of elements (C, D) to be drilled stacked at least partially with each other and define respectively a first and a second through channel (13, 16) available in use coaxially with each other to be engaged by a drill bit (P) of the drill (A); adjustable distance constraint means (40) connecting the first and second operating units (11, 12) and selectively operable to adjust the distance between the first and second operating units (11, 12) to a value correlated with or corresponding to the thickness of the at least partially stacked element (D) or elements (C, D) to be drilled; and a channeling system (41) connecting the first and second channels (13, 16) with a suction source to allow in use the suction of dust and scraps generated by the drill (A).
B23Q 11/00 - Accessoires montés sur les machines-outils pour maintenir les outils ou les organes de la machine dans de bonnes conditions de travail ou pour refroidir les pièces travaillées; Dispositifs de sécurité spécialement combinés aux machines-outils, disposés dans ces machines ou spécialement conçus pour être utilisés en relation avec ces machines
B23Q 9/00 - Agencements pour le support ou le guidage d'appareils ou de machines portatifs pour le travail du métal
B08B 15/04 - Précautions prises pour empêcher les crasses ou les fumées de s'échapper de la zone où elles sont produites; Ramassage ou enlèvement des crasses ou fumées de cette zone provenant d'un espace restreint, p.ex. d'un outil
B23B 47/34 - Agencements pour enlever les copeaux des trous pendant le perçage; Agencements fixés à l'outil pour briser les copeaux
A rotor (8, 8', 106''', 106'''', 106''''', 106'''''') for an aircraft (1, 100) is described, comprising an input shaft (10, 108) rotatable around a first axis (C, I); an output member (15, 112) rotatable around a second axis (D, J); a coupling element (20, 20', 20'', 20''') functionally interposed between the input shaft (10, 108) and the output member (15, 112) and adapted to transmit the motion from the input shaft (10, 108) to the output member (15, 112); the coupling element (20, 20', 20'', 20''') is configured to allow, in use, a fixed or variable inclination between the respective first and second axes (C, I, D, J); the coupling element (20, 20', 20'', 20''') comprises at least a first corrugated element (21, 22, 25, 120''', 121''', 120'''', 121'''', 122'''') made of an elastically deformable material; the first corrugated element (21, 22, 25; 120''', 121'''; 120'''', 121'''', 122'''') allows the inclination through elastic deformation.
F16D 3/70 - Accouplements extensibles, c. à d. avec moyens permettant le mouvement entre parties accouplées durant leur entraînement avec pièces d'accouplement reliées par un ou plusieurs organes intermédiaires comportant des éléments élastiques disposés dans des trous pratiqués dans l'une des pièces d'accouplement et entourant des broches portées par l'autre pièce d'accouplement
F16D 21/02 - Systèmes comportant plusieurs embrayages actionnés mécaniquement pour relier de différentes manières trois arbres ou plus, ou d'autres organes de transmission
F16D 3/62 - Accouplements extensibles, c. à d. avec moyens permettant le mouvement entre parties accouplées durant leur entraînement avec pièces d'accouplement reliées par un ou plusieurs organes intermédiaires comportant des tringles de poussée ou de traction reliées à la fois aux deux parties les tringles ou leurs fixations étant élastiques
F16D 3/72 - Accouplements extensibles, c. à d. avec moyens permettant le mouvement entre parties accouplées durant leur entraînement avec pièces d'accouplement reliées par un ou plusieurs organes intermédiaires avec des fixations aux pièces d'accouplement axialement espacées
F16D 3/74 - Accouplements extensibles, c. à d. avec moyens permettant le mouvement entre parties accouplées durant leur entraînement avec pièces d'accouplement reliées par un ou plusieurs organes intermédiaires avec des fixations aux pièces d'accouplement axialement espacées l'organe ou les organes intermédiaires étant en caoutchouc ou faits d'un autre matériau flexible
F16D 3/50 - Accouplements extensibles, c. à d. avec moyens permettant le mouvement entre parties accouplées durant leur entraînement avec pièces d'accouplement reliées par un ou plusieurs organes intermédiaires
B64C 27/22 - Giravions complexes, c. à d. aéronefs utilisant en vol à la fois les caractéristiques de l'avion et celles du giravion
A helicopter (1) is described comprising a motor member (3) comprising an output shaft (12) and a first stator (11, 29) rotatably supporting the output shaft (12) around a first axis (C); a main rotor (4) adapted to provide the lift necessary for the support and the thrust necessary for the movement of the helicopter (1); a transmission (7) interposed between the motor member (3) and the main rotor (4); the transmission (7) comprises, in turn, an input shaft (21) rotatable around a second axis (D) and a second stator (20, 30) rotatably supporting the input shaft (21) around the second axis (D); the helicopter (1) also comprises a joint (35) interposed between the first and second stator (11, 29; 20, 30), angularly fixed with respect to the first axis (C), and configured to allow an inclination between the first and second stator (11, 29; 20, 30) in a plane parallel to said first axis (C); the joint (35) comprises a first corrugated element (36) made of an elastically deformable material, interposed between said first and second stator (11, 29; 20, 30), and adapted to allow the inclination through elastic deformation.
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 27/14 - Entraînement direct entre groupe propulseur et moyeu du rotor
F16D 3/72 - Accouplements extensibles, c. à d. avec moyens permettant le mouvement entre parties accouplées durant leur entraînement avec pièces d'accouplement reliées par un ou plusieurs organes intermédiaires avec des fixations aux pièces d'accouplement axialement espacées
F16D 3/74 - Accouplements extensibles, c. à d. avec moyens permettant le mouvement entre parties accouplées durant leur entraînement avec pièces d'accouplement reliées par un ou plusieurs organes intermédiaires avec des fixations aux pièces d'accouplement axialement espacées l'organe ou les organes intermédiaires étant en caoutchouc ou faits d'un autre matériau flexible
71.
THRUST REVERSER FOR TURBOFAN PROPULSION SYSTEM OF AN AIRCRAFT AND THRUST REVERSAL METHOD
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
72.
AIRCRAFT CAPABLE OF HOVERING AND METHOD FOR TRANSPORTING A LOAD SUSPENDED FROM SUCH AIRCRAFT
There is described an aircraft (1) configured to be able to hover, comprising a fuselage (2); and a support element (13, 55) adapted to support a load (10, 51), made of elastically deformable material and constrained to said fuselage (2); the support element (13, 55) being movable in an operating position in which it is arranged at least partially outside said fuselage (2) and supports said load (10, 51); the aircraft (1) comprises a sock (20, 60) surrounding the support element (13, 55) arranged in said operating position; the sock (20, 60) is configured to contain the elastic return of the support element (13, 55), in case the support element (13, 55) arranged in said operating position is sheared off.
A method of realization of an aeronautical item with hybrid composite materials by means of additive technology comprising the steps of: design of the product by means of a three-dimensional mathematical model which defines, in a reference system, the shape and dimensions and includes the information associated with the areas of the item that must be reinforced according to the level of stress; deposition, by means of additive technology, of a matrix in polymeric material and of reinforcing fibers according to the mathematical model; deposition of one or more continuous fibers made of different materials along articulated paths in correspondence with the areas that must be reinforced according to the level of stress (continuous fibers oriented along paths defined by the directions of the loads or in any case in the directions provided in the design phase).
B29C 64/118 - 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]
B29C 64/393 - Acquisition ou traitement de données pour la fabrication additive pour la commande ou la régulation de procédés de fabrication additive
B29C 70/38 - Empilage automatisé, p.ex. utilisant des robots, par application de filaments selon des modèles prédéterminés
G06F 30/20 - Optimisation, vérification ou simulation de l’objet conçu
B64C 1/00 - Fuselages; Caractéristiques structurales communes aux fuselages, voilures, surfaces stabilisatrices ou organes apparentés
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 multifunctional composite material comprises a polymeric matrix filled with electrically conductive nanoparticles combined with a self-healing molecular filler selected in the group consisting of molecules and oligomers containing groups acting as donors and acceptors of hydrogen bonds.
C08L 63/00 - Compositions contenant des résines époxy; Compositions contenant des dérivés des résines époxy
H01B 1/24 - Matériau conducteur dispersé dans un matériau organique non conducteur le matériau conducteur comportant des compositions à base de carbone-silicium, du carbone ou du silicium
A fixed-wing aircraft (1) provided with a fuselage (3) which extends along a longitudinal axis (L), a pair of wings, a propulsion system and a vertical stabilizer (5) provided with a vertical drift (6) fixed with respect to the fuselage (3), The drift (6) has a through seat (8) which houses at least one thrust generator (12) adapted to produce in a controllable manner an air flow (F) along a transverse axis (T) from a first side of the drift (6) or from a second side of the drift opposite the first one, producing aerodynamic forces which act on the opposite faces (6a, 6b) of the drift (6) and are used for the directional control of the aircraft (1).
B64C 11/00 - Hélices, p.ex. du type caréné; Caractéristiques communes aux hélices et aux rotors pour giravions
B64C 15/14 - Commande de l'assiette, de la direction du vol ou de l'altitude par jets réactifs les jets étant autres que les jets propulsifs principaux
78.
SYNCHRONOUS ELECTRIC GENERATOR AND METHOD FOR CONTROLLING THE FREQUENCY AND THE AMPLITUDE OF THE INDUCED VOLTAGE ON THE STATOR WINDINGS OF THE SYNCHRONOUS GENERATOR THEREOF
H02P 6/32 - Dispositions pour la commande de moteurs à champ enroulé, p.ex. de moteurs avec bobines d’excitation
H02P 9/30 - Dispositions pour la commande de génératrices électriques de façon à obtenir les caractéristiques désirées à la sortie par variation du champ utilisant des tubes à décharge ou des dispositifs à semi-conducteurs utilisant des dispositifs à semi-conducteurs
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).
A rotor (3, 4) for an aircraft (1) is described having: a support (9) angularly fixed with respect to an axis (B, C) and housing a power source (20); a unit (11, 12) rotatable about axis (B, C) and housing an electrical load (21, 24) of the resistive type; and a power supply system (19, 19', 19'', 19''', 19'''', 19''''', 19'''''', 19''''''') for the electrical load (21, 24) and comprising: a first transformer (22) electrically interposed between the power source (20) and the load (21, 24); the first transformer (22) comprises: a first winding (26) arranged on the support (9) and a second winding (28) arranged on the unit (11, 12, 13), a stator (9) carried by the support (9), rotationally fixed with respect to axis (B, C) and to which the first winding (26) is fixed; and a rotor (101) operatively connected to the unit (11, 12) and to which the second winding (28) is fixed; the power supply system (19, 19', 19'', 19''', 19'''', 19''''', 19'''''', 19''''''') comprises a capacitive circuit (50) electrically connected to the first transformer (22), so as to reduce the reactive power absorbed by the rotary transformer (22).
A helicopter (1) is described comprising: a tail boom (7); a fin (8) projecting from the tail boom (7); and a tailplane (9) arranged at the tail boom (7) and transversal to the fin (8); at least one of the fin (8) and the tailplane (9) defining a first aerodynamic surface (10, 11) generating a first aerodynamic force; at least one first element (20, 90) transversal to the first aerodynamic surface (10, 11); and a second aerodynamic surface (21, 92) generating a second aerodynamic force, connected to the first element (20, 90), facing and spaced from the first aerodynamic surface (10, 11); the second aerodynamic surface (21, 92) is spaced from the other of the fin (8) and the tailplane (9).
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
An aircraft (1) is described comprising a transmission unit (9) with a first module (11, 13, 15) and a lubrication system (25, 25'); the first module (11, 13, 15) comprises a casing (20) and a movable member (17, 18, 19); the lubrication system (25, 25') comprises a header (26), a nozzle (27, 28) fed with the lubricating fluid and designed to feed the lubricating fluid inside the casing (20) of the first module (11, 13, 15), a collection tank (30, 100') for the lubricating fluid injected by the nozzle (27, 28), and recirculation means (35) designed to cause the recirculation of the lubricating fluid from the collection tank (30, 100') to the feed header (26); the first module (11, 13, 15) comprises a valve (60, 60') available in a first configuration, in which it enables the outflow of said lubricating fluid from said module (11) to the recirculation means (35) when the pressure of the lubricating fluid inside the header (26) is greater than a threshold value; and in a second configuration, in which it fluidically isolates the module (11) from the recirculation means (35) when the pressure of the lubricating fluid inside the header (26) is less than the threshold value.
B64C 27/14 - Entraînement direct entre groupe propulseur et moyeu du rotor
B64C 27/00 - Giravions; Rotors propres aux giravions
B64D 35/00 - Transmission de la puissance du groupe moteur aux hélices ou aux rotors; Aménagements des transmissions
B64D 35/04 - Transmission de la puissance du groupe moteur aux hélices ou aux rotors; Aménagements des transmissions caractérisée par le fait que la transmission entraîne plusieurs hélices ou rotors
B64D 35/08 - Transmission de la puissance du groupe moteur aux hélices ou aux rotors; Aménagements des transmissions caractérisée par le fait que la transmission est entraînée par plusieurs groupes moteurs
B64C 27/22 - Giravions complexes, c. à d. aéronefs utilisant en vol à la fois les caractéristiques de l'avion et celles du giravion
A convertiplane (1, 1', 1'') is described that comprises: a fuselage (2), having a first longitudinal axis (A) and, in turn, comprising a nose (12) and a tail portion (13); a pair of wings (3) arranged on respective opposite sides of the fuselage (2), carrying respective rotors (5) and generating a lift value; and a pair of engines (4) operatively connected to respective rotors (5); each rotor (5) comprising a mast (9) rotatable about a second axis (B) between a helicopter configuration and an aeroplane configuration; each rotor (4) is interposed between the fuselage (2) and the relative rotor (5) along the direction of extension of the relative wing (3).
B64C 29/00 - Aéronefs capables d'atterrir ou de décoller à la verticale, p.ex. aéronefs à décollage et atterrissage verticaux [ADAV, en anglais VTOL]
B64D 27/14 - Aéronefs caractérisés par le type ou la position des groupes moteurs du type à turbine à gaz à l'intérieur du fuselage ou fixés à celui-ci
B64D 27/24 - Aéronefs caractérisés par le type ou la position des groupes moteurs utilisant la vapeur, l'électricité ou l'énergie de ressorts
B64C 3/56 - Repliage ou rabattement pour réduire l'encombrement de l'aéronef
B64D 27/12 - Aéronefs caractérisés par le type ou la position des groupes moteurs du type à turbine à gaz à l'intérieur de la voilure ou fixés à celle-ci
B64C 1/14 - Fenêtres; Portes; Trappes d'évacuation ou panneaux de visite; Structures de cadres environnants; Verrières; Pare-brise
B64D 1/06 - Mécanismes de largage des bombes; Trappes de la soute à bombes
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
B64D 27/02 - Aéronefs caractérisés par le type ou la position des groupes moteurs
84.
MULTI-BEAM ON RECEIVE ELECTRONICALLY-STEERABLE ANTENNA
A Multi-Beam on Receive Electronically Steerable Antenna (1) comprising a Tx array (2, 6) comprising a phased array of Tx antenna elements (3, 7) and having a geometric aperture with one or more pairs of parallel opposite sides; and an Rx array (2, 4) comprising a phased array of Rx antenna elements (3, 5) and having a geometric aperture with one or more pairs of parallel opposite sides. One or more pairs of parallel opposite sides of the geometric aperture of the Tx array (2, 6) are inclined relative to one or more pairs of parallel opposite sides of the geometric aperture of the Rx array (2, 4).
H01Q 21/06 - Réseaux d'unités d'antennes, de même polarisation, excitées individuellement et espacées entre elles
H01Q 21/28 - Combinaisons d'unités ou systèmes d'antennes sensiblement indépendants et n’interagissant pas entre eux
H01Q 25/00 - Antennes ou systèmes d'antennes fournissant au moins deux diagrammes de rayonnement
G01S 7/28 - DÉTERMINATION DE LA DIRECTION PAR RADIO; RADIO-NAVIGATION; DÉTERMINATION DE LA DISTANCE OU DE LA VITESSE EN UTILISANT DES ONDES RADIO; LOCALISATION OU DÉTECTION DE LA PRÉSENCE EN UTILISANT LA RÉFLEXION OU LA RERADIATION D'ONDES RADIO; DISPOSITIONS ANALOGUES UTILISANT D'AUTRES ONDES - Détails des systèmes correspondant aux groupes , , de systèmes selon le groupe - Détails des systèmes à impulsions
H01Q 21/22 - Réseaux d'unités d'antennes, de même polarisation, excitées individuellement et espacées entre elles les unités d'antennes du réseau étant excitées d'une façon non uniforme en amplitude ou en phase, p.ex. réseau à prises ou réseau bidirectionnel
H01Q 3/26 - Dispositifs pour changer ou faire varier l'orientation ou la forme du diagramme de directivité des ondes rayonnées par une antenne ou un système d'antenne faisant varier la distribution de l’énergie à travers une ouverture rayonnante
A convertiplane (1, 1', 1 '') is described that comprises a fuselage (2), having a first longitudinal axis (A), with a nose (12) and a tail portion (13); a pair of wings (3) arranged on respective opposite sides of said fuselage (2), carrying respective rotors (5); a pair of engines (4) operatively connected to respective said rotors (5); at least one first lifting surface (19, 16) arranged on said tail portion (13); and a pair of canards (14) arranged on said nose (12) of said fuselage (2) and defining respective second lifting surfaces adapted to generate a third lift/negative lift value; each rotor (5) comprising a mast (9) rotatable about a second axis (B) and about an relative third axis (E) transversal to said second axis (B) and with respect to the fuselage (2), so as to set said convertiplane (1, 1', 1'') between a helicopter configuration and an aeroplane configuration; each second axis (B), in use, being transversal to the first axis (A) of said convertiplane (1, 1', 1'') in said helicopter configuration and being parallel to said first axis (A) in said aeroplane configuration.
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
A method is described for the folding of a convertiplane (1) with a fuselage (2) having a first axis (A), a pair of wings (3) and a pair of rotors (5) arranged on respective mutually opposite sides of the respective wings (3); each rotor (5) comprises a mast (9) rotatable about a second axis (B) and a plurality of blades (8a, 8b); each wing (3) comprises a first portion (20) fixed with respect to the fuselage (2); a second tip portion (21) opposite to the first portion (20); and a third intermediate portion (22), which is interposed between the associated first portion (20) and second tip portion (21); the mast (9) of each rotor (5) is integrally tiltable with the second axis (B) and associated second tip portion (21) about a third axis (E) transversal to the second axis (B) and the fuselage (2) so as to set said convertiplane (1) between a helicopter configuration and an aeroplane configuration; the method comprises the steps i) of arranging the convertiplane (1) in the helicopter configuration and ii) rotating a pair of assemblies (23) of respective wings (3) with respect to the fuselage (2) and the associated first portion (20) about respective fifth axes (I), so as to arrange the convertiplane (1) in a stowage configuration. A convertiplane (1) is also disclosed.
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
B64C 3/56 - Repliage ou rabattement pour réduire l'encombrement de l'aéronef
B64C 29/00 - Aéronefs capables d'atterrir ou de décoller à la verticale, p.ex. aéronefs à décollage et atterrissage verticaux [ADAV, en anglais VTOL]
87.
SYSTEM AND METHOD FOR MEASURING A DEFORMATION OF A STRUCTURE OF AN AIRCRAFT
A system for measuring a deformation of a structure arranged to be installed on an aircraft is described, comprising: - deformation sensor means which are arranged to be associated with the structure and to assume an electrical resistance value indicative of the deformation of this structure and which include two electrical connection terminals which are short-circuited so as to recreate a closed circuit; - magnetic field excitation means which are arranged to generate a magnetic field concatenated with the closed circuit, so as to generate an induced current, and which include a laser generator; - electromagnetic radiation transmission means included in the closed circuit, arranged to emit an electromagnetic radiation of which the value is a function of the electrical resistance of the deformation sensor means, and including an antenna; - electromagnetic radiation receiving means including an antenna and arranged to receive the electromagnetic radiation transmitted by the electromagnetic radiation transmission means; - control means arranged to determine the deformation of the structure as a function of the value of electromagnetic radiation received.
G01B 5/30 - Dispositions pour la mesure caractérisées par l'utilisation de techniques mécaniques pour mesurer la déformation dans un solide, p.ex. indicateur de déformation mécanique
G01B 7/16 - Dispositions pour la mesure caractérisées par l'utilisation de techniques électriques ou magnétiques pour mesurer les déformations dans un solide, p.ex. au moyen d'une jauge de contrainte à résistance
G01L 1/20 - Mesure des forces ou des contraintes, en général en faisant usage des cellules électrocinétiques, c. à d. des cellules contenant un liquide, dans lesquelles un potentiel électrique est produit ou modifié par l'application d'une contrainte
G01M 5/00 - Examen de l'élasticité des structures ou ouvrages, p.ex. fléchissement de ponts ou d'ailes d'avions
G08C 17/00 - Dispositions pour transmettre des signaux caractérisées par l'utilisation d'une voie électrique sans fil
G08C 23/00 - Systèmes de transmission de signaux non électriques, p.ex. systèmes optiques
H04B 5/00 - Systèmes de transmission à induction directe, p.ex. du type à boucle inductive
88.
CLOSURE SYSTEM OF THE INTERCONNECTION OF TRANSPORT UNITS CONNECTED TO EACH OTHER IN A CONVOY
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 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
B62D 55/24 - Chenilles du type à flexibilité totale, p.ex. à courroies de caoutchouc
F16C 29/08 - Dispositions pour couvrir ou protéger les chemins de roulement
B65G 47/66 - Plates-formes ou tasseaux fixes, p.ex. ponts entre transporteurs
A handle (10) for opening and closing a door of an aircraft, the handle comprising a base part (14) lockable to a rotatable shaft (11) of an opening mechanism of the door, a hand gripping part (15) connected to the base part (14), and a hinge (13) connecting the base part (14) to the gripping part (15) to allow relative rotation of the gripping part (15) with respect to the base part (14) about a first axis (E). One seat (16) is integral with the base part (14) and at least one other seat (17) is integral with the gripping part (15), the seats being adjacent and aligned along a second axis (F) parallel to the first axis (E). A mechanical fuse element of constraint is received in the seats (16, 17), such that by applying to the gripping part (15) a bending stress around the hinge (13) greater than a predetermined threshold, the element (18) of constraint shears between the seats (16, 17).
A roller unit (13) for moving a slat of an aircraft wing is adjustable in height and axial position to adjust the gap (G) between the idle roller (14) and a guide (10) integral with the slat. The roller is carried by an eccentric pin (24) having a stem portion (25) with a threaded portion (31) and an axially grooved end portion (30). A threaded annular element (54) cooperates with the threaded portion (31) of the stem portion to define a desired axial position of the roller. An anti-rotation annular element (57) is coupled in an axially slidable manner with the grooved end portion (30) of the stem portion and may be coupled with the threaded annular element (54) to prevent the rotation thereof on the threaded portion (31) of the stem portion (25). The threaded annular element (54) and the anti-rotation element (57) are tightened together between a pair of nuts (50, 61).
configDPpilotasset;extcodconfigDPpilotassetextconfigDPpilotassetextsuppmissmissionframeconfigDPpilotassetextmissionframemem,visualmem,visualvisualvisualvisual) 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
A rotor (3, 3', 3'') for an aircraft (1) is described that has a mast (150), an attenuating device (7, 7', 7'') to attenuate the transmission of vibrations from the mast (150) in a plane orthogonal to the first axis (A); and a transmission device (15) interposed between the mast (150) and the attenuating device (7, 7', 7''); the attenuating device (7, 7', 7'') comprises a first and a second mass unit (8, 9) with a first and a second mass (10, 11) rotatable about the first axis (A) with a first and a second rotational speed ((N-1)*Ω; (N+1)*Ω); (N+1)*Ω; (N-1)*Ω)), two control units (40, 40') operable to cause an additional rotation of at least one of the first and second masses (10, 11); and a first and a second support assembly (41, 41'; 42, 42') carrying the first and second masses (10; 11); each control unit (40, 40') controls the angle between the first and second masses (10, 11) and each control unit (40, 40') comprises: a belt (50) coupled to the support assembly (41, 41'; 42, 42') and a drive unit (51, 51') coupled to the first belt (50), to cause the rotation of the first support assembly (41, 41'; 42, 42') with respect to said transmission device (15).
A rotor (3, 3') for an aircraft (1) is described that has a mast (50), an attenuating device (7, 7') to attenuate the transmission of vibrations from the mast (50) in a plane orthogonal to the first axis (A), and a transmission device (15) interposed between the mast (50) and the attenuating device (7, 7'); the attenuating device (7; 7') comprises a first and a second mass unit (8, 9) with a first and a second mass (10, 11) rotatable about the first axis (A) with a first and a second rotational speed ((N-1)*Ω; (N+1)*Ω), two control units (40) operable to cause an additional rotation of at least one of the first and second masses (10, 11), and a first and a second support assembly (41, 42) carrying the first and second masses (10, 11); each control unit (40) controls the angle between the first and second masses (10, 11) and comprises a set of drive gear teeth (55, 55') integral with the first support assembly (41, 42), a cogwheel (56) with a set of control gear teeth (57) meshing with the drive gear teeth (55, 55'), and an actuator (58) to cause the rotation of the cogwheel (56) about a second axis (F) and of the first mass (10, 11) about said first axis (A).
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).
An anti-torque rotor (4) is described comprising: a mast (6) rotatable about a first axis (A); a plurality of blades (8) hinged on the mast (6) and rotatable about respective second axes (B) to vary the respective angles of attack; a control element (16) sliding along the first axis (A) with respect to the mast (6), rotatable with the mast (6) and connected to the blades (8) to cause the rotation about the second axes (B); a control mechanism (10), axially sliding and angularly fixed with respect to the mast (6); and a connection element (17) interposed between the control mechanism (10) and the control element (16), sliding integrally with the control mechanism (10) along the mast (6); the control mechanism (10) comprises a first and a second rod (60, 61); the rotor (4) comprises a coupling (70), which is configured to enable/prevent rotation of the second rod (61) with respect to the first rod (60) when the torque exerted by the first connection element (17) on the second rod (61) about the first axis (A) is greater/less than a threshold value in the event of failure of the connection element (17).
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 27/59 - Transmissions, p.ex. en liaison avec les moyens déclenchant ou agissant sur les pales mécaniques
An anti-torque rotor (4) is described comprising: a mast (6) rotatable about a first axis (A); a plurality of blades (8) rotatable about respective second axes (B); an element (16) slidable along the first axis (A) with respect to the mast (6), rotating integrally with the mast (6) and operatively connected to the blades (8); a control rod (10) slidable along axis (A); a first bearing (17) with a first ring (30) rotating integrally with element (16), a second ring (31) radially internal to the first ring (30) with respect to the first axis (A) and a plurality of first rolling bodies (32); a third ring (50) sliding integrally with the control rod (10) along the first axis (A) and angularly fixed with respect to the first axis (A); and a locking element (55) arranged in a standard configuration, in which it prevents the relative rotation of the second and third rings (31, 50) and movable from the standard configuration to at least one emergency configuration, in which it renders the second ring (31) free to rotate with respect to the third ring (50), when the first bearing (17) is in a failure condition.
B64C 27/78 - Mécanismes pour la commande du réglage ou du mouvement de la pale par rapport à la tête du rotor, p.ex. mouvement de traînée en conjonction avec le réglage du pas des pales du rotor anticouple
B64C 27/605 - Transmissions, p.ex. en liaison avec les moyens déclenchant ou agissant sur les pales mécaniques comportant un plateau oscillant, des mécanismes à tringlerie ou à came
An anti-torque rotor (4) is described for a helicopter (1), comprising: a mast (6) rotatable about a first axis (A); a plurality of blades (8) hinged on the mast (6), extending along respective second axes (B) transversal to said first axis (A) and rotatable about respective said second axes (B) to alter the respective angles of attack; a control element (16) sliding and rotating with respect to the mast (6), and operatively connected to said blades (8) to cause the rotation of said blades (8) about respective second axes (B) following a translation of said element (16) along the first axis (A); a control rod (10) sliding axially along first axis (A) with respect to the mast (6) and angularly fixed with respect to the first axis (A); and a connection element (17) interposed between the control rod (10) and the control element (16), sliding along the first axis (A) with respect to the mast (6) and integrally with the control rod (10); the anti-torque rotor (4) further comprises an interface (18, 93) made of an antifriction material interposed between said control rod (10) and said connection element (17).
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 27/59 - Transmissions, p.ex. en liaison avec les moyens déclenchant ou agissant sur les pales mécaniques
B64C 27/605 - Transmissions, p.ex. en liaison avec les moyens déclenchant ou agissant sur les pales mécaniques comportant un plateau oscillant, des mécanismes à tringlerie ou à came
B64C 27/78 - Mécanismes pour la commande du réglage ou du mouvement de la pale par rapport à la tête du rotor, p.ex. mouvement de traînée en conjonction avec le réglage du pas des pales du rotor anticouple
B64C 11/32 - Mécanismes de changement de pas des pales mécaniques
F16C 39/02 - Allégement de la charge appliquée aux paliers par moyens mécaniques
F16C 21/00 - Combinaisons de paliers à contact lisse avec des roulements à billes ou à rouleaux pour mouvement de rotation exclusivement
F16C 19/52 - Paliers à contact de roulement pour mouvement de rotation exclusivement avec dispositifs affectés par des conditions anormales ou indésirables
B64C 27/54 - Mécanismes pour la commande du réglage ou du mouvement de la pale par rapport à la tête du rotor, p.ex. mouvement de traînée
An anti-torque rotor (4, 4') is described that comprises: a mast (6) rotatable about a first axis (A); a plurality of blades (8) extending along respective second axes (B); a control element (16) sliding along the first axis (A) with respect to the mast (6), integrally rotatable with said mast (6), and connected to said blades (8); a control rod (10) sliding axially along first axis (A) and angularly fixed with respect to said first axis (A); a connection element (17) interposed between the control rod (10) and the control element (16), sliding along the first axis (A) integrally with the control rod (10), and configured to enable the relative rotation of said control element (16) with respect to the control rod (10) about the first axis (A); and a transmission unit (45) available in an active configuration or an inactive configuration; the transmission unit (45), in turn, comprises: an annular ridge (61) axially and angularly integral with the control rod (10) and radially projecting from the control rod (10); and a seat (64) engaged by the ridge (61) and angularly integral with the control element (16).
B64C 27/78 - Mécanismes pour la commande du réglage ou du mouvement de la pale par rapport à la tête du rotor, p.ex. mouvement de traînée en conjonction avec le réglage du pas des pales du rotor anticouple
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
A rotor (3) for a hover-capable aircraft (1) is described that comprises: a hub (5) rotating about an axis (A) and, in turn, comprising a plurality of blades (9), a mast (6) connectable to a power unit of the aircraft (1) and operatively connected to the hub (5) to drive the hub (5) in rotation about said axis (A), and an attenuating device (15) to attenuate the transmission of vibrations from the mast (6) to the aircraft (1) parallel to said (A); the attenuating device (15), in turn, comprising a casing (20), a first mass (21) free to oscillate parallel to said axis (A) with respect to the casing (20) and elastically connected to the casing (20), a second mass (25) free to oscillate parallel to said axis (A), connection means (30) adapted to make the first and second masses (21, 25) integrally movable along said axis (A) when the angular speed (Ω) of the mast (6) assumes a first value (Ω1), and actuator means (35) activatable to decouple the first and second masses (21, 25) when the angular speed (Ω) of the mast (6) assumes a second value (Ω2), different from the first value (Ω1).
B64C 27/00 - Giravions; Rotors propres aux giravions
F16F 15/26 - Compensation des forces d'inertie dans les systèmes à vilebrequins utilisant des masses solides autres que les pistons ordinaires, se déplaçant avec le système lui-même
F16F 7/10 - Amortisseurs de vibrations; Amortisseurs de chocs utilisant un effet d'inertie
F16F 7/116 - Amortisseurs de vibrations; Amortisseurs de chocs utilisant un effet d'inertie l'élément d'inertie étant monté de manière élastique sur des ressorts métalliques
100.
VERTICAL TAKE-OFF AND LANDING AIRCRAFT AND RELATED CONTROL METHOD
An aircraft (1, 1', 1''', 1'''', 1''''', 1'''''', 1''''''', 1'''''''', 1''''''''', 1'''''''''', 1''''''''''', 1'''''''''''', 1''''''''''''') capable of vertical take-off and landing is described, comprising a first propulsion unit (6a, 6b, 6c, 6d, 6e, 6f; 6a, 6b, 6g', 6h', 6c, 6d, 6e, 6i', 6j', 6f; 6a, 6c; 6d, 6f) configured to generate a first thrust (T1, T2, T3, T4, T5, T6; T1, T2, T7, T8, T3, T4, T5, T9, T10, T6; T1, T3, T4, T6) directed along a first axis (E, F, G, H, I, J; E, F, K, L, G, H, I, M, N, J; E, G, H, J); a second propulsion unit (6a, 6b, 6c, 6d, 6e, 6f; 6a, 6b, 6g', 6h', 6c, 6d, 6e, 6i', 6j', 6f; 6a, 6c; 6d, 6f) configured to generate a second thrust (T1, T2, T3, T4, T5, T6; T1, T2, T7, T8, T3, T4, T5, T9, T10, T6; T1, T3, T4, T6) directed along a second axis (E, F, G, H, I, J; E, F, K, L, G, H, I, M, N, J; E, G, H, J); the first propulsion unit and the second propulsion unit (6a, 6b, 6c, 6d, 6e, 6f; 6a, 6b, 6g', 6h', 6c, 6d, 6e, 6i', 6j', 6f; 6a, 6c; 6d, 6f) can be operated independently of one another; the first axis and second axis (E, F, G, H, I, J; E, F, K, L, G, H, I, M, N, J; E, G, H, J) are inclined to one another with respect to a first longitudinal direction (Y) of the aircraft (1, 1', 1''); the first axis and the second axis (E, F, G, H, I, J; E, F, K, L, G, H, I, M, N, J; E, G, H, J) are fixed with respect to the aircraft (1, 1', 1'').
B64C 29/00 - Aéronefs capables d'atterrir ou de décoller à la verticale, p.ex. aéronefs à décollage et atterrissage verticaux [ADAV, en anglais VTOL]
B64C 27/20 - Giravions caractérisés par le fait qu'ils possèdent des rotors haubanés, p.ex. plates-formes volantes
B64C 27/26 - Giravions complexes, c. à d. aéronefs utilisant en vol à la fois les caractéristiques de l'avion et celles du giravion caractérisé par le fait qu'il est doté d'ailes fixes
brevets
