Imaging system which may operate in conjunction with a single platform and may include a single plural-purpose imaging payload including at least a first optical path dedicated to a first imaging mission defining a first line of sight for the payload; and/or a second optical path dedicated to a second imaging mission defining a second light of sight for the payload which differs from the first line of sight; and/or a payload orientation subsystem, including a hardware processor, for selectably bringing the imaging payload into at least a first orientation yielding the first line of sight and/or a second orientation yielding the second line of sight, to yield a single platform configured to execute plural imaging missions including the first and second imaging missions.
H04N 23/58 - Moyens permettant de modifier le champ de vision de la caméra sans déplacer le corps de la caméra, p. ex. par nutation ou pivotement des optiques ou des capteurs d'images
G01C 11/02 - Dispositions de prises de vues spécialement adaptées pour la photogrammétrie ou les levers photographiques, p. ex. pour commander le recouvrement des photos
G02B 26/08 - Dispositifs ou dispositions optiques pour la commande de la lumière utilisant des éléments optiques mobiles ou déformables pour commander la direction de la lumière
Method for defending an area from vehicular threats in the area's vicinity, comprising detection of threat scenarios including vehicular threats in the area's vicinity in real time or near-real time; and/or controlling multiple interceptors to intercept at least some of the vehicular threats as detected; and/or using a machine learning hardware processor, trained on training data which may pair scenario outcomes to given mission plans which operated on given threat scenarios, to generate at least one mission plan for the interceptors, and/or to feed said mission plans to the interceptor control processor, in real time.
F41H 11/02 - Installations ou systèmes de défense anti-aérienne ou antimissiles
G05D 1/00 - Commande de la position, du cap, de l'altitude ou de l'attitude des véhicules terrestres, aquatiques, aériens ou spatiaux, p. ex. utilisant des pilotes automatiques
B64U 101/16 - Véhicules aériens sans pilote spécialement adaptés à des utilisations ou à des applications spécifiques à la guerre conventionnelle ou électronique à la commande, à la capture ou à l’immobilisation d’autres véhicules
G05D 1/10 - Commande de la position ou du cap dans les trois dimensions simultanément
G06N 3/006 - Vie artificielle, c.-à-d. agencements informatiques simulant la vie fondés sur des formes de vie individuelles ou collectives simulées et virtuelles, p. ex. simulations sociales ou optimisation par essaims particulaires [PSO]
G05D 1/69 - Commande coordonnée de la position ou du cap de plusieurs véhicules
G05D 1/12 - Commande pour la recherche d'un objectif
G05D 101/15 - Détails des architectures logicielles ou matérielles utilisées pour la commande de la position utilisant des techniques d’intelligence artificielle [IA] utilisant l’apprentissage automatique, p. ex. les réseaux neuronaux
3.
USE OF HIGH-RESOLUTION IMAGES TO ENABLE ARTIFICIAL INTELLIGENCE IDENTIFICATION OF SHIPS
A method of object detection comprises: (A) receive image(s) captured by imaging device(s) mounted on a waterborne platform. They comprise object(s) which are located within a body of water; (B) perform the following: (i) a low-resolution detection process comprising: (1) receive reduced resolution image(s), generated by performing resolution reduction; (2) object detection, utilizing a neural network, obtaining detected object(s). (ii) a high-resolution detection process based on splitting of image(s) to image tiles, comprising: (1) receive a set of tiles, derived from the image(s). Each tile corresponds to a sub-section of the image(s). Spatial resolution of each tile is higher than the reduced spatial resolution of the reduced resolution image(s); (2) a tile-based detection of objects, on tiles, utilizing image tiles neural network(s), obtaining tile-based detected object(s); (iii) merge the detected object(s) at reduced resolution and the tiles-based object(s), obtaining a final set of detected objects.
G06V 10/82 - Dispositions pour la reconnaissance ou la compréhension d’images ou de vidéos utilisant la reconnaissance de formes ou l’apprentissage automatique utilisant les réseaux neuronaux
A cover includes a housing (including a body and a wire positioning arrangement), fixing member, and sealing wire arrangement. The body covers a connection port preventing external access thereto independently of the housing, and includes a fixing bore having a bore axis and a removal path. The wire positioning arrangement, associated with the fixing bore, includes eyelets joined to the body and spaced apart in transverse arrangement re the removal path. In use, the fixing member fixedly engages the housing with respect to a connection port mounting structure via the fixing bore, covering the connection port, and is removable from the fixing bore via the removal path. In use, a sealing wire is positioned via the eyelets in an obstructing position with respect to the removal path, preventing passage of the fixing member therethrough. The sealing wire arrangement maintains in a tamper-proof manner the sealing wire in the obstructing position.
H01R 13/639 - Moyens additionnels pour maintenir ou verrouiller les pièces de couplage entre elles après l'engagement
G01R 11/24 - Dispositions pour éviter ou indiquer un usage frauduleux
F16B 41/00 - Dispositions contre la perte des boulons, écrous, broches ou goupillesDispositions empêchant toute action non autorisée sur les boulons, écrous, broches ou goupilles
G09F 3/03 - Formes ou structures de sceaux de sécurité
A method for use in designing a radome and respective radome structure are presented. The method comprising: providing data on physical shape of the radome, and data on one or more convergence points within said radome; determining general propagation paths mapping propagation of radiation from said one or more convergence points, and one or more selected angular ranges for emission from at least one of said convergence points; determining intersection of said external shape and said mapping of the general propagation paths, within at least said one or more selected angular ranges, and determining one or more tessellated layers for said radome. Wherein cross-section of elements of said one or more tessellated layer with said general propagation path of radiation emitted from the respective convergence location is constant within said one or more selected angular ranges.
There are provided systems and methods comprising obtaining a given image of a sequence of images acquired by a sensor and given metadata associated with the given image, wherein the given metadata comprise data informative of the given image, obtaining at least one synthetic entity whose representation depends on said at least part of the given metadata, and generating a training image which comprises the given image, or an image derived from said given image, and said at least one synthetic entity, wherein the training image is associated with a label informative of the at least one synthetic entity.
G06V 10/774 - Génération d'ensembles de motifs de formationTraitement des caractéristiques d’images ou de vidéos dans les espaces de caractéristiquesDispositions pour la reconnaissance ou la compréhension d’images ou de vidéos utilisant la reconnaissance de formes ou l’apprentissage automatique utilisant l’intégration et la réduction de données, p. ex. analyse en composantes principales [PCA] ou analyse en composantes indépendantes [ ICA] ou cartes auto-organisatrices [SOM]Séparation aveugle de source méthodes de Bootstrap, p. ex. "bagging” ou “boosting”
G06V 10/82 - Dispositions pour la reconnaissance ou la compréhension d’images ou de vidéos utilisant la reconnaissance de formes ou l’apprentissage automatique utilisant les réseaux neuronaux
G06V 20/40 - ScènesÉléments spécifiques à la scène dans le contenu vidéo
G06F 18/214 - Génération de motifs d'entraînementProcédés de Bootstrapping, p. ex. ”bagging” ou ”boosting”
G06V 10/40 - Extraction de caractéristiques d’images ou de vidéos
A deployment system pivotably deploys panel elements between a stowed configuration and a deployed configuration. Actuator(s) associated with each pair of panel elements include a first bracket mountable to one panel element, a second bracket mountable to the other panel element, and a linear motion to rotary motion converter (LMRMC) for pivoting the first bracket with respect to the second bracket responsive to a predetermined datum linear displacement being applied to the LMRMC. An actuation cable, coupled to each actuator, can be displaced linearly with respect thereto between a first position, corresponding to the stowed configuration, and a second position, corresponding to the deployed configuration, responsive to operation of the drive unit, such as to apply at least a corresponding datum linear displacement to the respective LMRMC of each actuator. The drive unit is configured for selectively displacing the actuation cable between the first position and the second position.
A heat transfer arrangement includes a first component, a second component, a dynamic connection arrangement, a moveable thermal interface, and a thermally activated spacer arrangement. The first and second components are mechanically connected by the dynamic connection arrangement, which allows the first and second components to remain mechanically connected while allowing the spacing therebetween to vary. The moveable thermal interface allows transitioning between first and second interface configurations, and the moveable thermal interface thermally couples and decouples, respectively, the first and second components with respect to one another. The thermally activated spacer arrangement is: mechanically and thermally coupled to the first component; mechanically decoupled from the second component; mechanically coupled to the moveable thermal interface; transitionable between first and second spacer configurations responsive to a first component temperature transitioning across a predetermined threshold temperature, thereby causing the moveable thermal interface to concurrently transition between the first and second interface configurations.
F28F 13/00 - Dispositions pour modifier le transfert de chaleur, p. ex. accroissement, diminution
B64G 1/50 - Aménagements ou adaptations des dispositifs de contrôle de l'environnement ou des conditions de vie pour la commande de la température
F28D 1/00 - Appareils échangeurs de chaleur comportant des ensembles de canalisations fixes pour une seule des sources de potentiel calorifique, les deux sources étant en contact chacune avec un côté de la paroi de la canalisation, dans lesquels l'autre source de potentiel calorifique est une grande masse de fluide, p. ex. radiateurs domestiques ou de moteur de voiture
F28F 21/08 - Structure des appareils échangeurs de chaleur caractérisée par l'emploi de matériaux spécifiés de métal
H01L 23/42 - Choix ou disposition de matériaux de remplissage ou de pièces auxiliaires dans le conteneur pour faciliter le chauffage ou le refroidissement
H01L 23/427 - Refroidissement par changement d'état, p. ex. caloducs
H05K 7/20 - Modifications en vue de faciliter la réfrigération, l'aération ou le chauffage
A deburring accessory (100) is coupled to a drill bit (10) to provide a drill bit assembly, thereby enabling deburring of a bore drilled by the drill bit. The deburring accessory (100) includes a base element (200) and at least one cutting insert (300) coupled to the base element. The base element (200) is non-rotatably and externally mounted to the drill bit (10). The cutting insert (300) has at least one respective cutting edge configured for deburring the bore, and is movably mounted with respect to the base element to allow relative movement between the cutting insert and the base element between stowed and deployed positions. In the stowed position the cutting insert is stowed within the base element. In the deployed position the cutting edge is projecting laterally with respect to the base element sufficiently such that, when coupled to the drill bit in the drill bit assembly, the cutting edge is capable of deburring the bore.
A system comprises a probe laser device configured to transmit a probe pulse towards an object, thereby obtaining a reflected probe pulse, a reorientation module including a film polarizer, a medium and a phase conjugate mirror, wherein a path of the reflected probe pulse from its reflection to the film polarizer is designated as a reflected probe path, wherein the reorientation module is operative to use the phase conjugate mirror to generate a phase conjugated reflected probe pulse, which is phase conjugated with the reflected probe pulse, receive, by the medium, the phase conjugated reflected probe pulse, and sequentially, a plurality of pump laser pulses, thereby generating, in the medium, a grating, reflect, using the grating, the plurality of pump laser pulses as a plurality of reoriented pump laser pulses each exiting the film polarizer along a path coinciding with the reflected probe path, to illuminate the object.
G02F 1/29 - Dispositifs ou dispositions pour la commande de l'intensité, de la couleur, de la phase, de la polarisation ou de la direction de la lumière arrivant d'une source lumineuse indépendante, p. ex. commutation, ouverture de porte ou modulationOptique non linéaire pour la commande de la position ou de la direction des rayons lumineux, c.-à-d. déflexion
G01S 17/66 - Systèmes de poursuite utilisant d'autres ondes électromagnétiques que les ondes radio
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 3/30 - Lasers, c.-à-d. dispositifs utilisant l'émission stimulée de rayonnement électromagnétique dans la gamme de l’infrarouge, du visible ou de l’ultraviolet utilisant des effets de diffusion, p. ex. l'effet Brillouin ou Raman stimulé
A radome structure and a corresponding method are described. The radome structure comprises one or more layers comprising at least one reinforced layer and at least one deformation absorbing layer positioned internally with respect to enclosed space of the radome structure to absorb deformation of the reinforced layer caused by projectile impact. The at least one deformation absorbing layer has predetermined thickness selected to absorb deformations caused by projectile impact within the reinforced layer, and wherein said reinforced layer is formed of a tough ductile material selected to deform upon impact by the projectile.
A VTOL aerial vehicle includes a body, a first propulsion system and a second propulsion system. The first propulsion system includes at least two first propulsion units, wherein the first propulsion system is pivotably mounted to the body and is configured for being selectively pivoted about a first pivot axis over a first pivot angle range with respect to the body. The second propulsion system includes at least two second propulsion units, wherein the second propulsion system is pivotably mounted to the body and is configured for being selectively pivoted about a second pivot axis over a second pivot angle range with respect to the body. The first propulsion system and the second propulsion system are configured for generating together sufficient thrust to enable vectored flight.
B64U 70/20 - Dispositions pour le lancement, le décollage ou l'atterrissage pour lancer ou capturer en vol les véhicules aériens sans pilote via un autre 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]
There is provided a system of displaying an augmented reality (AR) image on a viewable surface of a vehicle, the system comprising a processing circuitry configured to: receive data indicative of a location of a target external to the vehicle; determine a line-of-sight to the target in accordance with, at least, an operator viewing position and an operator viewing orientation; and control a scanning projector to display the AR image on a location of the viewable surface that is located substantially along the line-of-sight.
G09G 3/00 - Dispositions ou circuits de commande présentant un intérêt uniquement pour l'affichage utilisant des moyens de visualisation autres que les tubes à rayons cathodiques
B60K 35/21 - Dispositions de sortie, c.-à-d. du véhicule à l'utilisateur, associées aux fonctions du véhicule ou spécialement adaptées à celles-ci utilisant une sortie visuelle, p. ex. voyants clignotants ou affichages matriciels
B60K 35/28 - Dispositions de sortie, c.-à-d. du véhicule à l'utilisateur, associées aux fonctions du véhicule ou spécialement adaptées à celles-ci caractérisées par le type d’informations de sortie, p. ex. divertissement vidéo ou informations sur la dynamique du véhiculeDispositions de sortie, c.-à-d. du véhicule à l'utilisateur, associées aux fonctions du véhicule ou spécialement adaptées à celles-ci caractérisées par la finalité des informations de sortie, p. ex. pour attirer l'attention du conducteur
G02B 26/08 - Dispositifs ou dispositions optiques pour la commande de la lumière utilisant des éléments optiques mobiles ou déformables pour commander la direction de la lumière
A VTOL-type air vehicle is transitioned from forward speed mode to hover mode via a transient path in transition mode. The air vehicle includes first and second propulsion systems, and high lift, mild stall fixed wings. The first propulsion system can provide a first thrust (sufficient for enabling powered aerodynamic flight) at a first thrust vector. The second propulsion system can provide a second thrust (sufficient for enabling vectored thrust flight) at a second thrust vector, which is spatially fixed with respect to the air vehicle at least during transitioning. The transient path includes, during transitioning, manipulating a first magnitude of angle of attack and a second magnitude of forward speed to provide a corresponding aerodynamic lift component, and concurrently manipulating a third magnitude of the second thrust to provide a vertical vectored thrust component corresponding to the first magnitude of angle of attack. A summation of the aerodynamic lift component and vertical vectored thrust component is sufficient for enabling the air vehicle to remain in controlled flight in transition mode.
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
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]
An explosive bolt system includes an explosive bolt and an initiator device. The explosive bolt includes a shank having a first longitudinal end, an opposed second longitudinal end, and a longitudinal axis. The explosive bolt is configured for securing two elements together between the first longitudinal end and the second longitudinal end. The shank includes an internal chamber accommodating a first layer of a high density first secondary explosive material, and further accommodating a second layer of a low density second secondary explosive material in arming communication with the first layer. The initiator device is positioned with respect to the explosive bolt such that the initiator device is in arming communication with the explosive bolt.
F16B 31/00 - Assemblages à vis spécialement modifiés en vue de résister à une charge de tractionBoulons de rupture
B64G 1/64 - Systèmes pour réunir ou séparer des véhicules spatiaux ou des parties de ceux-ci, p. ex. aménagement pour l'accostage ou l'amarrage
F42B 3/00 - Cartouches de sautage, c.-à-d. enveloppes avec explosif
F42C 15/34 - Dispositifs d'armement des fuséesDispositifs de sécurité pour empêcher l'explosion prématurée des fusées ou des charges dans lesquels l'action de sécurité ou d'armement est effectuée au moyen d'un organe de blocage placé dans la chaîne pyrotechnique ou explosive entre l'amorce et la charge explosive
16.
PILOT TRAINING SYSTEM UTILIZING INTEGRATED REAL/VIRTUAL AIRCRAFT AND OBJECT DATA
There is provided a system of monitoring an airborne training aircraft, the system comprising a processing circuitry configured to: a) receive, from one or more ground- based aircraft simulators, data indicative of, at least, respective three-dimensional (3D) positions and bearings of one or more virtual aircraft associated with the respective simulators; b) receive, from the training aircraft, data indicative of, at least, the training aircraft's 3D position and bearing; c) construct, utilizing, at least, the training aircraft's 3D position and bearing, and the respective three-dimensional (3D) positions and bearings of respective virtual aircraft, at least one of: i) imaging depicting a view, from an external point of reference, of the training aircraft and relative positions of virtual aircraft, and ii) imaging depicting at least one instrument of the training aircraft, wherein the depicted at least one instrument depicts positions of the one or more virtual aircraft relative to training aircraft.
A system for identifying spoofers affecting a platform, including a hardware processor configured for, at least once, providing a time-specific spoof indication including using at least plural GNSS drift indications to compute plural drift-indication specific possible spoof alerts respectively, and/or combining the drift-indication specific possible spoof alerts to yield the time-specific spoof indication.
G01S 19/49 - Détermination de position en combinant ou en commutant entre les solutions de position dérivées du système de positionnement par satellite à radiophares et les solutions de position dérivées d'un autre système l'autre système étant un système de position inertielle, p. ex. en hybridation lâche
A boom member for in-flight refueling includes a first boom member portion, a second boom member portion, and a connect/disconnect mechanism. The first boom member portion includes a first boom lumen, a first boom axis, and a fuel receiving end. The second boom member portion includes a second boom lumen, a second boom axis, and a fuel delivery end including a fuel delivery nozzle. The connect/disconnect mechanism is configured for: selectively enabling the first boom member portion to be connected with respect to the second boom member portion to provide a connected configuration; and, for selectively enabling actively disconnecting the first boom member portion with respect to the second boom member portion to provide a disconnected configuration responsive to receiving a disconnection activation signal.
A coupler is provided for a circular connector having first and second cylindrical connection elements, the coupler including a first coupler element, a second coupler element and an engagement arrangement. When the first coupler element and the second coupler element are connected to the first connection element and the second connection element, respectively, the engagement arrangement is configured to permit axial translation of the first and second connection elements along the common connector axis into a connected configuration, conditional on at least a number of conditions for engagement being fulfilled.
A system which scans a Field of Regard (FOR) for target objects (aka targets), the system comprising a multi-beam illuminator which typically generates a multi-beam comprising plural beams, typically differentially coded according to a coding scheme, which respectively illuminate plural zones typically within the FOR; and/or a detector which may know the coding scheme and may, accordingly, detect which of the plural zones within the FOR, the target objects illuminated by the multi-beam belong to; and/or a scanner which controls the multi-beam to scan the FOR, to yield a high throughput scanning & detection system, which may be useful for large FOR applications, which may determine which target objects are present in, e.g., each of the plural zones.
A system for monitoring a safety coupling, the safety coupling including a visual failure indicator provided by a manufacturer thereof, the system includes: a processing circuitry configured for: receiving image data from the at least one optical sensor, the image data including data of a region of interest of the safety coupling and devoid of the visual failure indicator of the safety coupling; analyzing the image data to detect a change in a relative position between a first and a second part of the safety coupling; evaluating health of the safety coupling by determining whether the detected change is a fault associated with a failure mode of the safety coupling; and outputting an indicator of said health of said safety coupling based on said evaluating.
The presently disclosed subject matter includes a computer method and system for predicting the state of a marine platform. It involves generating platform response vectors based on environmental data and platform state data across multiple degrees of freedom (DOF) after wave impact and training a machine learning model using the multiple platform response vectors. During the prediction procedure, recorded wave data is used to create a waves-snapshot, process the wave data to determine wave parameters, apply these to the ML model to generate platform response vectors, and aggregate these vectors to predict the platform state following wave impact.
An air vehicle includes a fuselage defining an air vehicle roll axis, a fixed wing arrangement in fixed spatial disposition with respect to the fuselage, and a propulsion system having at least four propulsion units. Each propulsion unit is mounted with respect to the wing system in lateral spaced relationship with respect to the roll axis, adjacent propulsion units being spaced circumferentially from one another. Each propulsion unit is configured for generating thrust along a respective thrust vector axis. Each thrust vector axis is in fixed inclined spatial orientation with respect to the roll axis such that the respective thrust has a non-zero thrust component defined on a plane orthogonal to the roll axis. Each non-zero thrust component has a respective non-zero moment arm with respect to the roll axis such as to provide a respective roll moment. Methods of controlling operation of an air vehicle are also provided.
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
B64C 29/02 - Aéronefs capables d'atterrir ou de décoller à la verticale, p. ex. aéronefs à décollage et atterrissage verticaux [ADAV, en anglais VTOL] dont l'axe matérialisant la direction du vol est vertical lorsque l'aéronef est au sol
B64U 10/20 - Aéronefs à décollage et atterrissage verticaux [ADAV, en anglais VTOL]
B64U 70/10 - Dispositions pour le lancement, le décollage ou l'atterrissage pour lancer ou capturer manuellement les véhicules aériens sans pilote
24.
VEHICLE NAVIGATION COMBINING TRANSMITTED OBJECT LOCATION INFORMATION AND SENSOR-BASED RELATIVE OBJECT LOCATION INFORMATION
A computerized positioning system is associated with a vehicle. It is configured to perform the following method: (a) receive first information indicative transmission(s), wherein the transmission is associated with an object(s). The first information comprises item(s) of object first position information associated with the object. The item of object first position information is indicative of an object absolute position. (b) receive second position information of the object, being indicative of a second relative position of the object with respect to the vehicle. (c) determine a derived position of the vehicle, based at least on the first information and on the second position information. The derived position is capable of being utilized to facilitate a correction in a reported position of the vehicle. The reported position is based on GNSS signal(s) received by GNSS receiver(s) associated with the vehicle.
G01S 19/48 - Détermination de position en combinant ou en commutant entre les solutions de position dérivées du système de positionnement par satellite à radiophares et les solutions de position dérivées d'un autre système
G01S 19/39 - Détermination d'une solution de navigation au moyen des signaux émis par un système de positionnement satellitaire à radiophares le système de positionnement satellitaire à radiophares transmettant des messages horodatés, p. ex. GPS [Système de positionnement global], GLONASS [Système mondial de satellites de navigation] ou GALILEO
G01S 19/40 - Correction de position, de vitesse ou d'attitude
25.
REAL-TIME CALCULATION OF GROUND TARGETING PARAMETERS USING TERRAIN ELEVATION DATA
A processor-based system of determining, in a moving aircraft, coordinates of a target, the system comprising a processing circuitry, the processor being operably connectable to a positioning system and a targeting system, the processor being configured to: receive, from the positioning system, data indicative of a current aircraft position; receive, from the targeting system, data indicative of a line-of-sight (LOS) vector from the cunent aircraft position to the target, and utilize a digital terrain elevation data (DTED) database to estimate a terrain point at which the received LOS vector meets a terrain surface location, thereby giving rise to data indicative of the coordinates of the target.
G01C 21/00 - NavigationInstruments de navigation non prévus dans les groupes
G01S 5/00 - Localisation par coordination de plusieurs déterminations de direction ou de ligne de positionLocalisation par coordination de plusieurs déterminations de distance
G01S 3/00 - Radiogoniomètres pour déterminer la direction d'où proviennent des ondes infrasonores, sonores, ultrasonores ou électromagnétiques ou des émissions de particules sans caractéristiques de direction
G01S 17/06 - Systèmes déterminant les données relatives à la position d'une cible
26.
AUTOMATIC GENERATION OF A FLIGHT PATH FOR TARGET ACQUISITION
A method comprising, by a processor and memory circuitry, for an aerial vehicle comprising a payload operative to perform an interaction with a target: for each target of a plurality of targets, determining an interaction area based on a position of the target, wherein, for each position of the aerial vehicle located in the interaction area of the target, the interaction between the payload and the target is enabled according to an operability criterion, generating a series of connections, wherein each connection comprises at least one waypoint located in an interaction area of a target of the plurality of targets and at least one waypoint located in an interaction area of another different target of the plurality of targets, wherein each interaction area comprises a waypoint of at least one connection of the series of connections, and obtaining a flight path for the aerial vehicle using the series of connections.
An impact attenuation device includes: a first chamber having a movably mounted piston element; a second chamber. The piston element includes first and second piston faces, and is configured for preventing fluid flow therethrough. The first chamber is in selective fluid communication with the second chamber via a rupture disc arrangement including a rupture disc having first and second disc faces. The rupture disc arrangement has a first configuration wherein the rupture disc prevents fluid communication between the first and second chambers. The rupture disc arrangement has a second configuration, in which the rupture disc is ruptured allowing such fluid communication, responsive to a predetermined threshold gauge pressure being applied between the first and second disc faces. The first chamber includes a first volume of incompressible fluid in contact with the first piston face and the first rupture disc face. The second chamber includes a second volume of compressible fluid.
F16F 9/06 - Ressorts, amortisseurs de vibrations, amortisseurs de chocs ou amortisseurs de mouvement de structure similaire, utilisant un fluide ou moyen équivalent comme agent d'amortissement utilisant à la fois un gaz et un liquide
F16F 7/00 - Amortisseurs de vibrationsAmortisseurs de chocs
An ejection module for ejecting a projectile includes a module forward end and a module aft end. The module forward end includes a central axis, and a module interface configured for selectively affixing the module to the projectile in a load-bearing manner, and for enabling selective disconnection between the module and the projectile. The module aft end includes a module propulsion system having a plurality of rocket motors and rocket propellant source. Each rocket motor: is laterally spaced with respect to the central axis; has a respective fixed thrust vector non-parallel with respect to the central axis; and is configured for generating a controllable level of respective thrust along the respective thrust vector, independently of the respective level of thrust generated by the other rocket motors along their respective thrust vectors. The module propulsion system is configured for enabling independently controlling the respective level of thrust of each rocket motor.
F41F 3/04 - Lanceurs de roquettes ou de torpilles pour roquettes
F42B 15/36 - Moyens de liaison entre le moteur-fusée et le corps d'une roquetteRaccords pour relier les différents étages d'une roquetteMoyens de désassemblage
F02K 9/58 - Soupapes d'alimentation en combustible
F02K 9/88 - Moteurs-fusées, c.-à-d. ensembles fonctionnels portant à la fois le combustible et son oxydantLeur commande caractérisés par la commande de la poussée ou du vecteur poussée utilisant des tuyères de fusées auxiliaires
29.
SYSTEM, METHOD AND COMPUTER PROGRAM PRODUCT FOR DETECTION OF GNSS JAMMERS
A system, computer program product and method facilitating safe motion of objects, comprising providing GNSS jammer detection functionality, including a hardware processor configured to detect jammers, to at least one networked fleet including plural moving objects, wherein at least one object has, aboard, GNSS functionality and a hardware processor, and wherein information indicative of at least one GNSS jammer position is shared between the plural moving objects.
A connection system is provided for releasably connecting a first component and a second component in a first direction parallel to a reference longitudinal axis, including one or more locking devices and an actuator. Each locking device has a geometrically locked configuration and an unlocked configuration. In the geometrically locked configuration the locking device is capable of reversibly geometrically locking together the first component and the second component in a mutually clamped relationship along the first direction, each locking device comprising at least two linkage elements pivotably mounted to one another about a common clamp axis. The actuator device is configured for transitioning each locking device from the geometrically locked configuration to the unlocked configuration by selectively applying to each respective locking device an unlocking force directly to the respective linkage elements at the respective common clamp axis, in a second direction parallel to a reference transverse axis.
A marine vessel management system, comprising: receiving input data comprising at least radar input data indicative of a first field of view and imagery input data indicative of a second field of view being at least partially overlapping with said first field of view. Processing the input data to determine data indicative of reflecting object(s) within an overlapping portion of said first field of view. Determining respective locations(s) within said second field of view, where said reflecting object(s) are identified, and obtaining radar meta-data of said reflecting object(s); processing said input imagery data said respective locations in an overlapping portion of said second field of view. Determining image data piece(s) corresponding with section(s) of said imagery data associated with said reflecting object(s). Using said radar meta-data for generating label data and generating output data comprising said image data section(s) and said label data.
G01S 7/41 - Détails des systèmes correspondant aux groupes , , de systèmes selon le groupe utilisant l'analyse du signal d'écho pour la caractérisation de la cibleSignature de cibleSurface équivalente de cible
B63B 35/00 - Embarcations ou structures flottantes similaires spécialement adaptées à des finalités spécifiques et non prévues ailleurs
G01S 13/86 - Combinaisons de systèmes radar avec des systèmes autres que radar, p. ex. sonar, chercheur de direction
G01S 13/937 - Radar ou systèmes analogues, spécialement adaptés pour des applications spécifiques pour prévenir les collisions d’embarcations
G05D 1/248 - Dispositions pour déterminer la position ou l’orientation utilisant des signaux fournis par des sources artificielles extérieures au véhicule, p. ex. balises de navigation générés par des satellites, p. ex. GPS
G05D 101/15 - Détails des architectures logicielles ou matérielles utilisées pour la commande de la position utilisant des techniques d’intelligence artificielle [IA] utilisant l’apprentissage automatique, p. ex. les réseaux neuronaux
G05D 107/00 - Environnements spécifiques des véhicules commandés
G06V 10/70 - Dispositions pour la reconnaissance ou la compréhension d’images ou de vidéos utilisant la reconnaissance de formes ou l’apprentissage automatique
G06V 20/56 - Contexte ou environnement de l’image à l’extérieur d’un véhicule à partir de capteurs embarqués
32.
AIR VEHICLE AND METHOD OF OPERATION OF AIR VEHICLE
An air vehicle has an airframe, aerodynamic lift-generating wings, and a propulsion system. The propulsion system provides propulsion to the air vehicle in powered aerodynamic flight mode and in vectored flight mode, and stability and control in vectored flight mode. The propulsion system includes a first set of non-pivotable first propulsion units, arranged in polygonal arrangement with respect to the airframe, enclosing the air vehicle center of gravity, providing a fixed vertical thrust vector and an aggregate vertical thrust sufficient for enabling vectored flight mode. The propulsion system includes a second set of pivotable second propulsion units, arranged in spaced relationship with respect to the center of gravity, and provide vectored control moments to the air vehicle in three rotational degrees of freedom. The second propulsion units enable angular displacement of the respective thrust vectors at least between a respective vertical position and a respective horizontal position, and provide at least an aggregate horizontal thrust sufficient for providing powered aerodynamic flight mode.
A system and method for tracking moving objects located within an area of interest are described. A sequence of periodic frames of the area is generated from LiDAR measurements. The sequence includes preliminary periodic and periodic operational frames. Each periodic frame includes point cloud data including static object data and dynamic object data. The static data are filtered out by applying a pattern mask generated by using the predetermined number of the preliminary periodic frames. For each periodic operational frame, clusters of points related to the dynamic object data are generated. Tracks of the moving objects are constructed from clusters related to the same object. The clusters are obtained for a predetermined number of the periodic operational frames. Each cluster is defined by a characteristics vector associated with a moving object in a corresponding periodic operational frame. Each characteristics vector includes cluster parameters associated with the corresponding moving object.
G01S 17/89 - Systèmes lidar, spécialement adaptés pour des applications spécifiques pour la cartographie ou l'imagerie
G06T 5/20 - Amélioration ou restauration d'image utilisant des opérateurs locaux
G06V 10/25 - Détermination d’une région d’intérêt [ROI] ou d’un volume d’intérêt [VOI]
G06V 10/762 - Dispositions pour la reconnaissance ou la compréhension d’images ou de vidéos utilisant la reconnaissance de formes ou l’apprentissage automatique utilisant le regroupement, p. ex. de visages similaires sur les réseaux sociaux
G06V 10/764 - Dispositions pour la reconnaissance ou la compréhension d’images ou de vidéos utilisant la reconnaissance de formes ou l’apprentissage automatique utilisant la classification, p. ex. des objets vidéo
A clamp band system includes a clamp band and a clamp loading system. The clamp band releasably couples a first flange of a first component with respect to a second flange of a second component, and includes a plurality of clamp elements (each having an engagement portion and an outer portion) and a peripheral band. The engagement portions are configured for engaging the first flange and the second flange in a clamping position. The band is configured for selectively peripherally engaging the outer portions in a band holding position, such as to enable the band to induce a predetermined frictional load on the outer portions, sufficient to hold the clamp elements in the clamping position. The clamp loading system selectively preloads the clamp elements in the clamping position and enables the band to adopt the band holding position subsequent to the clamp elements being preloaded in the clamping position.
B64G 1/64 - Systèmes pour réunir ou séparer des véhicules spatiaux ou des parties de ceux-ci, p. ex. aménagement pour l'accostage ou l'amarrage
F16L 23/06 - Raccords à brides les brides étant raccordées par des organes tendus dans le plan radial raccordées par leviers à mouvement de rotule
F16L 23/08 - Raccords à brides les brides étant raccordées par des organes tendus dans le plan radial raccordées par broche et écrou fileté disposés tangentiellement
F16L 33/04 - Colliers de serrage pour manches serrés par broche et écrou filetés disposés tangentiellement
F16B 2/08 - Brides ou colliers, c.-à-d. dispositifs de fixation dont le serrage est effectué par des forces effectives autres que la résistance à la déformation inhérente au matériau dont est fait le dispositif externes c.-à-d. agissant par contraction utilisant des frettes ou des bandes
The presently disclosed subject matter includes a method and system for determining position of vehicles operating in a formation, a process referred to herein as "range-based mapping". This task is accomplished by measuring the ranges between different vehicles in the formation to thereby obtain range-data, sharing the range-data between the different vehicles in the formation, and calculating the relative position of the vehicles in the formation based on the compilation of range data, including both self-measured range data and range-data obtained from other vehicles in the formation.
G01C 21/16 - NavigationInstruments de navigation non prévus dans les groupes en utilisant des mesures de la vitesse ou de l'accélération exécutées à bord de l'objet navigantNavigation à l'estime en intégrant l'accélération ou la vitesse, c.-à-d. navigation par inertie
G01C 21/20 - Instruments pour effectuer des calculs de navigation
G05D 1/10 - Commande de la position ou du cap dans les trois dimensions simultanément
A propulsion system, including a rotor arrangement rotatably mounted with respect to a nacelle about a rotor axis. The rotor arrangement includes rotor blades, each being pivotably mounted to a hub element about a respective blade pivot axis, the rotor blades being deployable between an undeployed configuration and a deployed configuration. The nacelle includes a nacelle body having a nacelle outer surface including facet elements and transition elements, each facet element extending aft from the hub element, each adjacent pair of facet elements being circumferentially spaced from one another by a corresponding transition element, each facet element having a first curvature with respect to the rotor axis, each transition element having a second curvature with respect to the rotor axis. The first curvature is different from the second curvature. In the undeployed configuration, each rotor blade is in overlying and fully external relationship with respect to a corresponding facet element.
There are provided systems and methods comprising, for an aerial vehicle comprising an image acquisition device coupled to a device enabling modification of an orientation of its line of sight, while the aerial vehicle is flying over a scene along a flight path corresponding to a hold pattern, operating the image acquisition device according to a first acquisition mode, said operating comprising controlling the device to move the image acquisition device according to a first motion pattern enabling the line of sight of the image acquisition device to be pointed towards different fractions of the scene at different instants of the given period of time, thereby enabling acquisition of the different fractions covering most or all of the scene at a desired image resolution, wherein each given fraction of the scene is acquired with a field of view which is smaller than the whole scene at the desired image resolution.
B64U 20/87 - Montage des dispositifs d’imagerie, p. ex. montage des suspensions à cardan
H04N 23/68 - Commande des caméras ou des modules de caméras pour une prise de vue stable de la scène, p. ex. en compensant les vibrations du boîtier de l'appareil photo
G01S 17/06 - Systèmes déterminant les données relatives à la position d'une cible
G06T 3/4038 - Création de mosaïques d’images, p. ex. composition d’images planes à partir de sous-images planes
A launch system is provided, including a composite vehicle and a carrier vehicle. The composite vehicle includes a payload vehicle, a booster vehicle and a first coupling system. The payload vehicle is configured for powered spaceflight at least in a space medium, and includes a rocket driven propulsion system. The booster vehicle is configured for powered supersonic/hypersonic aerodynamic flight, includes a ramjet propulsion system, and is configured for transporting the composite vehicle between a first altitude and a second altitude under propulsive power provided by the ramjet propulsion system. The first coupling system is configured for selectively coupling and decoupling the payload vehicle with respect to the booster vehicle. The carrier vehicle is configured at least for powered subsonic/transonic/supersonic aerodynamic flight, and for transporting the composite vehicle to at least the first altitude from a ground location. The launch system also includes a second coupling system for selectively coupling and decoupling the composite vehicle with respect to the carrier aircraft.
B64D 5/00 - Aéronefs transportés par un aéronef porteur, p. ex. pour être largués ou repris en vol
B64G 1/64 - Systèmes pour réunir ou séparer des véhicules spatiaux ou des parties de ceux-ci, p. ex. aménagement pour l'accostage ou l'amarrage
F02K 7/14 - Ensembles fonctionnels dans lesquels le fluide de travail est utilisé uniquement sous forme de jet, c.-à-d. ensembles ne comportant ni turbine ni autre moteur entraînant un compresseur ou une soufflante carénéeLeur commande caractérisés par une compression dans un diffuseur, c.-à-d. tubulures aéro-thermodynamiques ou statoréacteurs à combustion externe, p. ex. statoréacteurs à combustion supersonique
A system including: an optical steering module configured to receive reflected light, which reflected light includes a portion of a probe light beam reflected from an object, the reflected light including light of a first polarization type, which optical steering module including; a first optical path allowing passage of light of the first polarization type; a second optical path, including an optical steering element, allowing passage of light of a second polarization type; an optical shot generation module optically connected to the optical steering module to receive light from the first optical path and including: a mirror configured to reverse an orientation of light received from the optical steering module, returning the light towards the optical steering module; and a polarization changing element configured to change light of the first polarization type to light of the second polarization type, light returning from the optical shot generation module to the optical steering module passing through the second optical path of the optical steering module; a processor configured to generate control signals for control of the optical steering element, based on a predicted position of the object, to steer light emitted from the second optical path towards the object.
G01S 17/66 - Systèmes de poursuite utilisant d'autres ondes électromagnétiques que les ondes radio
G01S 17/46 - Détermination indirecte des données relatives à la position
B23K 26/02 - Mise en place ou surveillance de la pièce à travailler, p. ex. par rapport au point d'impactAlignement, pointage ou focalisation du faisceau laser
G01S 17/00 - Systèmes utilisant la réflexion ou la reradiation d'ondes électromagnétiques autres que les ondes radio, p. ex. systèmes lidar
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
G01S 17/06 - Systèmes déterminant les données relatives à la position d'une cible
G01S 3/782 - Systèmes pour déterminer une direction ou une déviation par rapport à une direction prédéterminée
A rotor blade is provided for a rotor having a rotor turning axis, the rotor blade having a blade aerodynamic section and a blade root extension. The blade root extension extends towards the rotor turning axis from the blade root of the blade aerodynamic to at least a free blade inboard edge, and includes a trailing section, a leading section and an engagement section. The engagement section is configured for being engaged to a rotor hub. The trailing section is at least partially co-extensive with respect to the engagement section in an inboard direction parallel to a blade span axis of the rotor blade. A rotor arrangement includes a plurality of such rotor blades and the hub element, and a propulsion assembly includes such a rotor arrangement and a drive unit.
A system for improving GNSS-based functioning of platforms, the system including a processor which provides, to a client, an estimate of current GNSS quality at a location occupied by a given platform, by, at least once, computing increasing functions of distances between GNSS-based estimated locations of the given platform, and locations estimated independently of the GNSS, for said given platform; and a processor which compares the estimate of current GNSS quality, for each vehicle in a fleet of interest to the client, to a GNSS quality target value, and, on at least one occasion in which a vehicle in the fleet of interest to the client is found to differ unacceptably from the GNSS quality target value, commands an actuator to take at least one corrective measure, yielding GNSS quality monitoring functionality.
A flight simulation system for enabling g-force training includes a seating system, a sensor arrangement, and a controller. The seating system is configured for accommodating a human occupant and for providing thereto physically simulated flight conditions corresponding to predetermined real flight conditions, the predetermined real flight conditions including g-forces, wherein the physically simulated flight conditions include application of non-g forces to the human occupant corresponding to the g-forces, and wherein the g-forces are considered sufficient to provide g-force induced physiological stress to the human occupant. The sensor arrangement is configured for providing real-time feedback data of predetermined physiological parameters of the human occupant, in operation of the flight simulation system with the human occupant accommodated in the seating system, wherein the predetermined physiological parameters are indicative of the g-force induced physiological stress. The controller is configured for controlling the seating system to provide the physically simulated flight conditions.
G09B 9/10 - 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 avec des moyens de simulation des forces générées par le vol ou par les moteurs sur l'occupant de l'aéronef
G09B 9/12 - Systèmes de déplacement pour simulateurs d'aéronef
G09B 9/30 - Simulation de vue à partir d'un aéronef
G08B 21/04 - Alarmes pour assurer la sécurité des personnes réagissant à la non-activité, p. ex. de personnes âgées
A61B 5/00 - Mesure servant à établir un diagnostic Identification des individus
An energy attenuation system for a seating system (having a bucket and a frame includes at least one energy attenuation component operatively coupled with a fuse system. The energy attenuation component includes first and second ends securable to the bucket and the frame, respectively. The fuse system includes a plurality of fuse elements and an engagement element. Each fuse element has a first and second fuse ends, and operates to break under a corresponding predetermined fixed load. The engagement element is movable with respect to the fuse elements and is engageable in a load bearing manner via the respective said second fuse ends thereof with any desired fuse element group chosen, each fuse element group including one or more fuse elements. The engagement element is securable to the bucket or the frame, and the first fuse ends of all the fuse elements are securable to the frame or bucket, respectively.
B60N 2/42 - Sièges spécialement adaptés aux véhiculesAgencement ou montage des sièges dans les véhicules à des fins particulières ou pour des véhicules particuliers le siège étant construit pour protéger son occupant des effets des forces d'accélération anormales, p. ex. sièges anticollision ou sièges de sécurité
B60N 2/427 - Sièges spécialement adaptés aux véhiculesAgencement ou montage des sièges dans les véhicules à des fins particulières ou pour des véhicules particuliers le siège étant construit pour protéger son occupant des effets des forces d'accélération anormales, p. ex. sièges anticollision ou sièges de sécurité le siège ou ses parties constitutives se déplaçant lors d'une collision
B64D 11/06 - Aménagements ou adaptations des sièges
45.
GENERATION OF TEMPORALLY CLOSE-PACKED LASER PULSES
A system for laser light control including: a loop, including: an optical amplifier having an amplifier input and an amplifier output; a splitter having: a splitter input configured to receive light from the amplifier output; a splitter first output configured to output light out of the loop; and a splitter second output configured so that the amplifier input receives light from the splitter second output; the splitter being configured to split light received at the splitter input into a first portion and a second portion respectively outputted at the splitter first output and the splitter second output; a pulse loop input configured to receive a laser pulse and to direct the laser pulse into the loop; where light takes a round-trip travel time to traverse an optical path around the loop including the optical amplifier, and the splitter; wherein the system is configured so that a light pulse received at the pulse loop input gives rise at the splitter first output to a pulse train comprising a plurality of light pulses separated in time from each other by a time related to the round-trip travel time.
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
46.
IMPROVED SYSTEM, METHOD AND COMPUTER PROGRAM PRODUCT FOR NORTH-FINDING
A system for finding a target direction, the system comprising a gyroscope and/or an accelerometer perpendicular to the gyroscope and/or a rotating stage on which the gyroscope and accelerometer are mounted, and/or a hardware processor configured for computing a first azimuthal orientation which points to a horizontal direction, based on readings taken when the gyroscope and accelerometer are in a first azimuthal position; and/or an estimation of a required direction based on: at least one gyroscope reading and at least one accelerometer reading in the first azimuthal position and/or at least one gyroscope reading and at least one accelerometer reading in a second, opposite azimuthal position 180 degrees away from the first position.
G01C 19/38 - Gyroscopes rotatifs pour indiquer une direction dans le plan horizontal, p. ex. compas gyroscopiques avec action de recherche du nord par des moyens autres que magnétiques, p. ex. gyrocompas utilisant la rotation de la terre
G01C 21/16 - NavigationInstruments de navigation non prévus dans les groupes en utilisant des mesures de la vitesse ou de l'accélération exécutées à bord de l'objet navigantNavigation à l'estime en intégrant l'accélération ou la vitesse, c.-à-d. navigation par inertie
An air intake module for a projectile includes a module forward end (MFE), a module aft end (MAE), and an aft facing intake cone arrangement (AFICA). The air intake module is configured for connection to the forward portion and the propulsion system of the projectile. The MAE is longitudinally displaceable with respect to the MFE between a stowed configuration (wherein the MFE is at a first spacing with respect to the MAE) and a deployed configuration (wherein the MFE is at a second spacing, greater than the first spacing). The AFICA includes a plurality of intake cone elements, each being pivotably movable between an open position (corresponding to the stowed configuration) wherein the intake cone elements are overlying the MAE, and a closed position (corresponding to the deployed configuration) wherein the intake cone elements are pivoted towards one another to form an aft facing cone structure forward of the MAE.
B64D 33/02 - Aménagement sur les aéronefs des éléments ou des auxiliaires des ensembles fonctionnels de propulsion, non prévu ailleurs des entrées d'air de combustion
There are provided examples of an enhanced cargo capacity aircraft, converted from a datum aircraft. The enhanced cargo capacity aircraft includes the datum aircraft and a cargo module. The datum aircraft includes at least a fuselage having a dorsal fuselage part. The cargo module is affixed to the datum aircraft, thereby converting the datum aircraft to the enhanced cargo capacity aircraft. The datum aircraft is designed for aerodynamic flight capability absent the cargo module. The enhanced cargo capacity aircraft is capable of aerodynamic flight. The cargo module provides enhanced cargo capacity to the datum aircraft. The cargo module includes an external aerodynamic fairing defining an internal cargo volume, and is configured for being conformally affixed in overlying relationship with respect to the dorsal fuselage part. The cargo module includes a cargo handling floor and at least one access door, and a cargo handling system configured for transporting and securing at least one cargo unit within the cargo volume. The cargo unit includes a standard unit load device (ULD).
B64C 1/22 - Autres structures faisant corps avec le fuselage pour faciliter le chargement
A62C 3/08 - Prévention, limitation ou extinction des incendies spécialement adaptées pour des objets ou des endroits particuliers dans les véhicules, p. ex. les véhicules routiers dans les avions
A system of wireless communication between a ground intercom of an aircraft and external systems comprises: a) an access door of a ground intercom access compartment of the aircraft, the door configured to be fixed to the compartment; b) a wireless ground intercom communications processing circuitry comprised in the door; and c) antenna(s) comprised in the door. The compartment comprises a ground intercom access panel, which comprises socket(s). The processing circuitry is operatively connectable to the ground intercom of the aircraft, via the panel, and to the antenna(s Plug(s) are connected to the processing circuitry, and are configured for plugging into the socket(s). This thereby enables retrofit of the system on an existing aircraft, by means of plugging the plug(s) into socket(s) of an existing ground intercom access panel of the aircraft. The system selectively provides wireless communication between the aircraft's ground intercom and the external system(s).
A computerized system performs training of machine learning models to enable prediction of occurrence of event(s), which are associated with a system to be analyzed. The system performs the following: (a) provide trained Anomaly Detection Model(s). (b) provide Analysis Tool(s), configured to provide quantitative indications of the event(s). The quantitative indications of the event(s) are based on input events(s). (c) receive first unlabeled data associated with the system, where this data comprise sensor data, (d) input the first unlabeled data to the Anomaly Detection Model(s). (d) generate, using the Anomaly Detection Models, indications of occurrence of the input event(s), based on the first unlabeled data, (e) input the indications of the occurrence into the Tool(s). (f) generate, using the Tools, quantitative indications of the events, based the indications of the occurrence, (g) generate, using the quantitative indications, labels for the first unlabeled data.
A method for use in designing a radome and respective radome structure are presented. The method comprising: providing data on physical shape of the radome, and data on one or more convergence points within said radome; determining general propagation paths mapping propagation of radiation from said one or more convergence points, and one or more selected angular ranges for emission from at least one of said convergence points; determining intersection of said external shape and said mapping of the general propagation paths, within at least said one or more selected angular ranges, and determining one or more tessellated layers for said radome. Wherein cross-section of elements of said one or more tessellated layer with said general propagation path of radiation emitted from the respective convergence location is constant within said one or more selected angular ranges.
H01Q 1/42 - Enveloppes non intimement mécaniquement associées avec les éléments rayonnants, p. ex. radome
H01Q 17/00 - Dispositifs pour absorber les ondes rayonnées par une antenneCombinaisons de tels dispositifs avec des éléments ou systèmes d'antennes actives
A deployment system pivotably deploys panel elements between a stowed configuration and a deployed configuration. Actuator(s) associated with each pair of panel elements include a first bracket mountable to one panel element, a second bracket mountable to the other panel element, and a linear motion to rotary motion converter (LMRMC) for pivoting the first bracket with respect to the second bracket responsive to a predetermined datum linear displacement being applied to the LMRMC. An actuation cable, coupled to each actuator, can be displaced linearly with respect thereto between a first position, corresponding to the stowed configuration, and a second position, corresponding to the deployed configuration, responsive to operation of the drive unit, such as to apply at least a corresponding datum linear displacement to the respective LMRMC of each actuator. The drive unit is configured for selectively displacing the actuation cable between the first position and the second position.
Refueling devices for use in in-flight refueling operation are provided, including a body configured for being towed by a tanker aircraft and having a boom member that has a fuel delivery nozzle, a spatial control system and a longitudinal control system. The longitudinal displacement control system includes at least one panel element defining a front panel projected area orthogonal to a body longitudinal axis, each panel element being controllably and reversibly deployable incrementally to each one of a plurality of successive deployed positions between a fully retracted position and a fully deployed position, to provide a respective reversible incrementally increasing aft force to the refueling device at least during the in-flight refueling operation.
According to the subject matter disclosed herein, an application miming on a network communication subsystem is assigned with at least one respective database, where data inputs received by the application induce a database update in the respective database. A database update automatically induces packaging of the updated data in a network message followed by transmission of the message to one or more other network communication subsystems connected to the same network. Likewise, in the other direction, an incoming network data-update message, received by the network communication subsystem, initiates a chain of events that cause a database update, which may ultimately affect the data provided to an application miming at the application layer.
H04L 67/1095 - Réplication ou mise en miroir des données, p. ex. l’ordonnancement ou le transport pour la synchronisation des données entre les nœuds du réseau
A wing system is provided for an air vehicle, the air vehicle having a fuselage including a fuselage longitudinal axis. The wing system includes a set of wings, configured for transitioning between a stowed configuration and a deployed configuration. The set of wings includes a first said wing having a first wing tip, a first wing longitudinal axis, and a first pivot axis; and a second said wing having a second wing tip, a second wing longitudinal axis, and a second pivot axis. The first pivot axis and the second pivot axis are non-coaxial. In the stowed configuration, the first wing and the second wing are in overlying relationship such that at least a majority of a pressure surface of one wing is facing a suction surface of the other wing, and the first wing tip is spaced from the second wing tip by a first lateral spacing. In the deployed configuration, the first wing is oriented with respect to the second wing such that the first wing tip is spaced from the second wing tip by a second lateral spacing greater than the first lateral spacing. The transitioning includes a pivoting operation, including: pivoting the first wing about the first pivot axis between the stowed configuration and the deployed configuration; and, pivoting the second wing about the second pivot axis between the stowed configuration and the deployed configuration.
A system for identifying spoofers affecting a platform e.g., vehicle, including a hardware processor configured for, at least once, providing a time-specific spoof indication including using at least plural GNSS drift indications to compute plural drift- indication specific possible spoof alerts respectively, and/or combining the drift-indication specific possible spoof alerts to yield the time-specific spoof indication.
G01S 19/49 - Détermination de position en combinant ou en commutant entre les solutions de position dérivées du système de positionnement par satellite à radiophares et les solutions de position dérivées d'un autre système l'autre système étant un système de position inertielle, p. ex. en hybridation lâche
G01S 19/48 - Détermination de position en combinant ou en commutant entre les solutions de position dérivées du système de positionnement par satellite à radiophares et les solutions de position dérivées d'un autre système
A method is provided for operating a parachute-payload system with respect to a predetermined target zone location. The method includes: providing the parachute-payload system; constructing a predicted descent trajectory for the parachute-payload system from a nominal start altitude to the target zone location based on meteorological data; and deploying the parachute-payload system to passively descend along a real descent trajectory, at least nominally corresponding to the predicted descent trajectory, starting at a chosen deployment location on the predicted descent trajectory.
B64D 1/08 - Largage ou éjection d'objets les objets étant des dispositifs porte-charges
G05D 1/10 - Commande de la position ou du cap dans les trois dimensions simultanément
G01C 21/20 - Instruments pour effectuer des calculs de navigation
G01P 5/00 - Mesure de la vitesse des fluides, p. ex. d'un courant atmosphériqueMesure de la vitesse de corps, p. ex. navires, aéronefs, par rapport à des fluides
G08G 5/02 - Aides pour l'atterrissage automatique, c. à d. systèmes dans lesquels les données des vols d'avions arrivant sont traitées de façon à fournir les données d'atterrissage
An explosive bolt system includes an explosive bolt and an initiator device. The explosive bolt includes a shank having a first longitudinal end, an opposed second longitudinal end, and a longitudinal axis. The explosive bolt is configured for securing two elements together between the first longitudinal end and the second longitudinal end. The shank includes an internal chamber accommodating a first layer of a high density first secondary explosive material, and further accommodating a second layer of a low density second secondary explosive material in arming communication with the first layer. The initiator device is positioned with respect to the explosive bolt such that the initiator device is in arming communication with the explosive bolt.
A wing system is provided for an air vehicle, the wing system having a stowed configuration, a pre-deployed configuration, and a deployed configuration. The wing system includes two wings, each wing having aerofoil profiles and being pivotably deployable about a respective pivot axis between the pre-deployed configuration and the deployed configuration. In the stowed configuration the two wings are in first general superposed spatial relationship with respect to one another and are capable of being accommodated within an envelope having an envelope cross-sectional profile and a corresponding envelope cross-sectional area. In the pre-deployed configuration, the two wings are in second general superposed spatial relationship with respect to one another and capable of deploying to the deployed configuration. In the deployed configuration the wings are each capable of generating aerodynamic lift in an airstream. Each aerofoil profile of each wing is a slotted aerofoil having a primary element, a secondary element and a chord, the secondary element being pivotable with respect to the primary element and spaced therefrom by a gap. Each aerofoil profile has a respective maximum thickness, and a respective maximum absolute thickness. In the stowed configuration, the respective second element of each aerofoil of one wing is set at a different flap angle as compared with the respective second element of each aerofoil of the other wing.
A VTOL-type air vehicle is transitioned from forward speed mode to hover mode via a transient path in transition mode. The air vehicle includes first and second propulsion systems, and high lift, mild stall fixed wings. The first propulsion system can provide a first thrust (sufficient for enabling powered aerodynamic flight) at a first thrust vector. The second propulsion system can provide a second thrust (sufficient for enabling vectored thrust flight) at a second thrust vector, which is spatially fixed with respect to the air vehicle at least during transitioning. The transient path includes, during transitioning, manipulating a first magnitude of angle of attack and a second magnitude of forward speed to provide a corresponding aerodynamic lift component, and concurrently manipulating a third magnitude of the second thrust to provide a vertical vectored thrust component corresponding to the first magnitude of angle of attack. A summation of the aerodynamic lift component and vertical vectored thrust component is sufficient for enabling the air vehicle to remain in controlled flight in transition mode.
There is provided a system of displaying an augmented reality (AR) image on a viewable surface of a vehicle, the system comprising a processing circuitry configured to: receive data indicative of a location of a target external to the vehicle; determine a line-of-sight to the target in accordance with, at least, an operator viewing position and an operator viewing orientation; and control a scanning projector to display the AR image on a location of the viewable surface that is located substantially along the line-of-sight.
G06V 20/58 - Reconnaissance d’objets en mouvement ou d’obstacles, p. ex. véhicules ou piétonsReconnaissance des objets de la circulation, p. ex. signalisation routière, feux de signalisation ou routes
G06T 19/00 - Transformation de modèles ou d'images tridimensionnels [3D] pour infographie
G06T 19/20 - Édition d'images tridimensionnelles [3D], p. ex. modification de formes ou de couleurs, alignement d'objets ou positionnements de parties
G06F 3/01 - Dispositions d'entrée ou dispositions d'entrée et de sortie combinées pour l'interaction entre l'utilisateur et le calculateur
A system comprises a probe laser device configured to transmit a probe pulse towards an object, thereby obtaining a reflected probe pulse, a reorientation module including a film polarizer, a medium and a phase conjugate mirror, wherein a path of the reflected probe pulse from its reflection to the film polarizer is designated as a reflected probe path, wherein the reorientation module is operative to use the phase conjugate mirror to generate a phase conjugated reflected probe pulse, which is phase conjugated with the reflected probe pulse, receive, by the medium, the phase conjugated reflected probe pulse, and sequentially, a plurality of pump laser pulses, thereby generating, in the medium, a grating, reflect, using the grating, the plurality of pump laser pulses as a plurality of reoriented pump laser pulses each exiting the film polarizer along a path coinciding with the reflected probe path, to illuminate the object.
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 3/30 - Lasers, c.-à-d. dispositifs utilisant l'émission stimulée de rayonnement électromagnétique dans la gamme de l’infrarouge, du visible ou de l’ultraviolet utilisant des effets de diffusion, p. ex. l'effet Brillouin ou Raman stimulé
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
B23K 26/04 - Alignement, pointage ou focalisation automatique du faisceau laser, p. ex. en utilisant la lumière rétrodiffusée
G02F 1/29 - Dispositifs ou dispositions pour la commande de l'intensité, de la couleur, de la phase, de la polarisation ou de la direction de la lumière arrivant d'une source lumineuse indépendante, p. ex. commutation, ouverture de porte ou modulationOptique non linéaire pour la commande de la position ou de la direction des rayons lumineux, c.-à-d. déflexion
G01S 17/66 - Systèmes de poursuite utilisant d'autres ondes électromagnétiques que les ondes radio
A boom member for in-flight refueling includes a first boom member portion, a second boom member portion, and a connect/disconnect mechanism. The first boom member portion includes a first boom lumen, a first boom axis, and a fuel receiving end. The second boom member portion includes a second boom lumen, a second boom axis, and a fuel delivery end including a fuel delivery nozzle. The connect/ disconnect mechanism is configured for: selectively enabling the first boom member portion to be connected with respect to the second boom member portion to provide a connected configuration; and, for selectively enabling actively disconnecting the first boom member portion with respect to the second boom member portion to provide a disconnected configuration responsive to receiving a disconnection activation signal.
B64D 39/06 - Raccordement de la tuyauterie à l'aéronefDébranchement de la tuyauterie de celui-ci
B64D 39/04 - Adaptations de la structure des tuyauteries
F16L 37/23 - Accouplements du type à action rapide dans lesquels l'assemblage est maintenu par des billes, rouleaux ou ressorts hélicoïdaux sous pression radiale entre parties au moyen de billes
According to one aspect of the presently disclosed subject there is provided a system implemented in a mobile carrier for determining a position of the mobile carrier by using a processing and memory circuitry (PMC) and a satellite communications on the move (SOTM) antenna system, being configured to maintain a communications link from a satellite communications (SATCOM) having a spatial position. The system is configured to obtain data indicative of the spatial position of the SATCOM, the estimated altitude of the mobile carrier and the direction of the antenna towards the SATCOM spatial position and to determine the position of the mobile carrier.
G01S 5/02 - Localisation par coordination de plusieurs déterminations de direction ou de ligne de positionLocalisation par coordination de plusieurs déterminations de distance utilisant les ondes radioélectriques
G01S 13/46 - Détermination indirecte des données relatives à la position
Examples of a refueling device for use in in-flight refueling operation are provided. In at least one example the refueling device includes a body, a boom member and a spatial control system. The body is configured for being towed by a tanker aircraft in a forward direction via a fuel hose at least during in-flight refueling operation, the body having a body longitudinal axis and a neutral point. The boom member is carried by the body. The boom member has a fuel delivery nozzle, the fuel delivery nozzle being configured for selectively engaging with a fuel receptacle in a receiver aircraft to enable fuel to be transferred from the fuel hose to the receiver aircraft during such in-flight refueling operation. The spatial control system is configured for selectively providing stability and control to the refueling device. At least during refueling operation the fuel delivery nozzle is longitudinally forward of the neutral point.
B64D 39/04 - Adaptations de la structure des tuyauteries
G05D 1/00 - Commande de la position, du cap, de l'altitude ou de l'attitude des véhicules terrestres, aquatiques, aériens ou spatiaux, p. ex. utilisant des pilotes automatiques
A wing system is provided for an air vehicle, the air vehicle having a fuselage including a fuselage section and a fuselage longitudinal axis, the wing system having at least one wing deployment module. Each wing deployment module includes a set of wing elements, including at least a first wing element having a first wing element longitudinal axis, and a second wing element having a second wing element longitudinal axis. Each wing deployment module is configured for selectively transitioning between a respective stowed configuration and a respective deployed configuration. In the stowed configuration, the first wing element and the second wing element are in overlying relationship such that the first wing element longitudinal axis and the second wing element longitudinal axis are nominally parallel with one another. In the deployed configuration, the first wing element is oriented with respect to the second wing element such that the first wing element longitudinal axis is non-parallel with respect to the second wing element longitudinal axis.
A clamping device includes a base element, a first clamping arrangement moveably mounted with respect to the base element, and a second clamping arrangement moveably mounted with respect to the base element. The first clamping arrangement is configured for providing a coupling displacement along a coupling axis responsive to an actuation displacement being applied to the first clamping arrangement along an actuation axis, the actuation axis being non-parallel with respect to the coupling axis. The second clamping arrangement is configured for providing an output displacement along an output axis responsive to the coupling displacement being applied to the second clamping arrangement along the coupling axis, the output axis being non-parallel to the coupling axis.
F16L 23/04 - Raccords à brides les brides étant raccordées par des organes tendus dans le plan radial
F16L 27/108 - Raccords réglablesRaccords permettant un déplacement des parties raccordées comportant uniquement une connexion flexible les extrémités des tuyaux étant assemblées au moyen d'un manchon flexible le manchon ayant la forme d'un soufflet avec uniquement une ondulation
F16B 2/08 - Brides ou colliers, c.-à-d. dispositifs de fixation dont le serrage est effectué par des forces effectives autres que la résistance à la déformation inhérente au matériau dont est fait le dispositif externes c.-à-d. agissant par contraction utilisant des frettes ou des bandes
F16L 17/04 - Raccords avec garnitures adaptées à une étanchéité par pression de fluide avec segments d'étanchéité disposés entre la surface extérieure du tuyau et la surface intérieure d'un manchon ou d'une douille le manchon étant fendu ou fractionné dans le sens longitudinal
68.
DISTRIBUTED RADAR SYSTEM AND METHOD OF OPERATION THEREOF
Distributed radar systems and techniques for processing data received from such distributed radar systems. The distributed radar systems may utilize data on beam spatial pattern for processing collected signals and determining direction of one or more reflection origins (e.g., one or more objects reflecting transmitted signal).
G01S 13/44 - Radar à monopulse, c.-à-d. à lobes simultanés
G01S 13/00 - Systèmes utilisant la réflexion ou la reradiation d'ondes radio, p. ex. systèmes radarSystèmes analogues utilisant la réflexion ou la reradiation d'ondes dont la nature ou la longueur d'onde sont sans importance ou non spécifiées
G01S 13/58 - Systèmes de détermination de la vitesse ou de la trajectoireSystèmes de détermination du sens d'un mouvement
H01Q 3/36 - 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 phase relative ou l’amplitude relative et l’énergie d’excitation entre plusieurs éléments rayonnants actifsDispositifs 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 faisant varier la phase par des moyens électriques avec des déphaseurs variables
The present disclosure provides a fuel-impermeable structural unit for use as a structural element of a fuel tank, including a multi-plies structure made of one or more composite material and polymers, and, a sealing polymeric film structurally bonded to and coating the entire surface of at least one face of the multi-plied structure. The polymeric film is integrated with an underlying external layer of said multi-plies structure, is impermeable to the fuel, is not reactive with the fuel, and can bind to an adhesive for fixing one or more rigid elements thereto.
B32B 41/00 - Dispositions pour le contrôle ou la commande des procédés de stratificationDispositions de sécurité
B32B 1/00 - Produits stratifiés ayant une forme non plane
B32B 3/12 - Produits stratifiés comprenant une couche ayant des discontinuités ou des rugosités externes ou internes, ou une couche de forme non planeProduits stratifiés comprenant une couche ayant des particularités au niveau de sa forme caractérisés par une couche discontinue, c.-à-d. soit continue et percée de trous, soit réellement constituée d'éléments individuels caractérisés par une couche d'alvéoles disposées régulièrement, soit formant corps unique dans un tout, soit structurées individuellement ou par assemblage de bandes indépendantes, p. ex. structures en nids d'abeilles
B32B 5/18 - Produits stratifiés caractérisés par l'hétérogénéité ou la structure physique d'une des couches caractérisés par le fait qu'une des couches contient un matériau sous forme de mousse ou essentiellement poreux
B32B 7/12 - Liaison entre couches utilisant des adhésifs interposés ou des matériaux interposés ayant des propriétés adhésives
B32B 25/08 - Produits stratifiés composés essentiellement de caoutchouc naturel ou synthétique comprenant du caoutchouc comme seul composant ou comme composant principal d'une couche adjacente à une autre couche d'une substance spécifique de résine synthétique
B32B 25/14 - Produits stratifiés composés essentiellement de caoutchouc naturel ou synthétique comprenant des copolymères dans lesquels les composants en caoutchouc prédominent
B32B 27/06 - Produits stratifiés composés essentiellement de résine synthétique comme seul composant ou composant principal d'une couche adjacente à une autre couche d'une substance spécifique
B32B 27/08 - Produits stratifiés composés essentiellement de résine synthétique comme seul composant ou composant principal d'une couche adjacente à une autre couche d'une substance spécifique d'une résine synthétique d'une sorte différente
B32B 27/40 - Produits stratifiés composés essentiellement de résine synthétique comprenant des polyuréthanes
B32B 37/12 - Procédés ou dispositifs pour la stratification, p. ex. par polymérisation ou par liaison à l'aide d'ultrasons caractérisés par l'usage d'adhésifs
70.
AIR VEHICLE AND METHOD FOR OPERATING THE AIR VEHICLE
An air vehicle is provided including a body, a primary propulsion unit mounted to the body, and a set of secondary propulsion units mounted to the body. The primary propulsion unit includes at least one primary rotor and is configured for providing at least a majority of a total vertical thrust required for enabling vectored thrust flight to the air vehicle. The set includes at least three said secondary propulsion units. The set is configured for providing variable vectored thrust at least sufficient for generating control moments for stability and control of the air vehicle. The set of secondary propulsion units includes at least one secondary propulsion unit pivotably mounted with respect to the body about a respective pivot axis and configured for pivoting about the pivot axis between at least a vertical mode and a horizontal mode, to respectively provide a thrust vector at least in a range between a vertical thrust vector and a horizontal thrust vector. The pivotable secondary propulsion units are further configured for providing at least horizontal propulsion to the air vehicle at least when not in vertical mode.
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]
G05D 1/08 - Commande de l'attitude, c. à d. élimination ou réduction des effets du roulis, du tangage ou des embardées
B64C 27/24 - Giravions complexes, c.-à-d. aéronefs utilisant en vol à la fois les caractéristiques de l'avion et celles du giravion avec pales du rotor fixes en vol de façon à agir comme surfaces de sustentation
B64C 19/00 - Dispositifs de commande des aéronefs non prévus ailleurs
A propulsion system is provided, including a rotor arrangement rotatably mounted with respect to a nacelle about a rotor axis. The rotor arrangement includes a plurality of rotor blades, each being pivotably mounted to a hub element about a respective blade pivot axis, the rotor blades being deployable between an undeployed configuration and a deployed configuration. The nacelle includes a nacelle body having a nacelle outer surface including a plurality of facet elements and a plurality of transition elements, each facet element extending aft from the hub element, each adjacent pair of facet elements being circumferentially spaced from one another by a corresponding transition element, each facet element having a first curvature with respect to the rotor axis, each transition element having a second curvature with respect to the rotor axis. The first curvature is different from the second curvature. In the undeployed configuration, each rotor blade is in overlying and fully external relationship with respect to a corresponding facet element.
A computerized positioning system is associated with a vehicle. It is configured to perform the following method: (a) receive first information indicative transmission(s), wherein the transmission is associated with an object(s). The first information comprises item(s) of object first position information associated with the object. The item of object first position information is indicative of an object absolute position, (b) receive second position information of the object, being indicative of a second relative position of the object with respect to the vehicle, (c) determine a derived position of the vehicle, based at least on the first information and on the second position information. The derived position is capable of being utilized to facilitate a correction in a reported position of the vehicle. The reported position is based on GNSS signal(s) received by GNSS receiver(s) associated with the vehicle.
G01S 19/46 - Détermination de position en combinant les mesures des signaux provenant du système de positionnement satellitaire à radiophares avec une mesure supplémentaire la mesure supplémentaire étant du type signal d'onde radioélectrique
G01S 19/48 - Détermination de position en combinant ou en commutant entre les solutions de position dérivées du système de positionnement par satellite à radiophares et les solutions de position dérivées d'un autre système
G01S 19/07 - Éléments coopérantsInteraction ou communication entre les différents éléments coopérants ou entre les éléments coopérants et les récepteurs fournissant des données pour corriger les données de positionnement mesurées, p. ex. DGPS [GPS différentiel] ou corrections ionosphériques
73.
AUTOMATIC GENERATION OF A FLIGHT PATH FOR TARGET ACQUISITION
A method comprising, by a processor and memory circuitry, for an aerial vehicle comprising a payload operative to perform an interaction with a target: for each target of a plurality of targets, determining an interaction area based on a position of the target, wherein, for each position of the aerial vehicle located in the interaction area of the target, the interaction between the payload and the target is enabled according to an operability criterion, generating a series of connections, wherein each connection comprises at least one waypoint located in an interaction area of a target of the plurality of targets and at least one waypoint located in an interaction area of another different target of the plurality of targets, wherein each interaction area comprises a waypoint of at least one connection of the series of connections, and obtaining a flight path for the aerial vehicle using the series of connections.
G05D 1/00 - Commande de la position, du cap, de l'altitude ou de l'attitude des véhicules terrestres, aquatiques, aériens ou spatiaux, p. ex. utilisant des pilotes automatiques
74.
SYSTEM, METHOD AND COMPUTER PROGRAM PRODUCT FOR DETECTION OF GNSS JAMMERS
A system, computer program product and method facilitating safe motion of objects, comprising providing GNSS jammer detection functionality, including a hardware processor configured to detect jammers, to at least one networked fleet including plural moving objects, wherein at least one object has, aboard, GNSS functionality and a hardware processor, and wherein information indicative of at least one GNSS jammer position is shared between the plural moving objects.
H04K 3/00 - Brouillage de la communicationContre-mesures
G01S 19/23 - Test, contrôle, correction ou étalonnage d'un élément récepteur
H04W 4/44 - Services spécialement adaptés à des environnements, à des situations ou à des fins spécifiques pour les véhicules, p. ex. communication véhicule-piétons pour la communication entre véhicules et infrastructures, p. ex. véhicule à nuage ou véhicule à domicile
H04W 28/02 - Gestion du trafic, p. ex. régulation de flux ou d'encombrement
A connection system is provided for releasably connecting a first component and a second component in a first direction parallel to a reference longitudinal axis, including one or more locking devices and an actuator. Each locking device has a geometrically locked configuration and an unlocked configuration. In the geometrically locked configuration the locking device is capable of reversibly geometrically locking together the first component and the second component in a mutually clamped relationship along the first direction, each locking device comprising at least two linkage elements pivotably mounted to one another about a common clamp axis. The actuator device is configured for transitioning each locking device from the geometrically locked configuration to the unlocked configuration by selectively applying to each respective locking device an unlocking force directly to the respective linkage elements at the respective common clamp axis, in a second direction parallel to a reference transverse axis.
F42B 15/36 - Moyens de liaison entre le moteur-fusée et le corps d'une roquetteRaccords pour relier les différents étages d'une roquetteMoyens de désassemblage
F42B 15/38 - Éléments explosifs en forme d'anneaux pour la séparation des différentes parties d'une roquette
B64G 1/64 - Systèmes pour réunir ou séparer des véhicules spatiaux ou des parties de ceux-ci, p. ex. aménagement pour l'accostage ou l'amarrage
F16L 37/20 - Raccords serrés par leviers à mouvement de rotule
76.
NAVIGATION SYSTEM AND METHOD WITH CONTINUOUSLY UPDATING ML
A marine vessel management system and method are described, comprising: receiving input data comprising at least radar input data indicative of a first field of view and imagery input data indicative of a second field of view being at least partially overlapping with said first field of view. Processing the radar input data to determine data indicative of one or more reflecting objects within an overlapping portion of said first field of view. Determining one or more respective locations within said second field of view, where said one or more reflecting objects are identified, and obtaining radar meta-data of said one or more reflecting objects; processing said input imagery data said respective locations in an overlapping portion of said second field of view. Determining one or more image data pieces corresponding with one or more sections of said imagery data associated with said one or more reflecting objects. Using said radar meta-data for generating label data and generating output data comprising said one or more image data sections and said label data. Thereby facilitating connection of said radar meta-data with image data of one or more objects to enable machine learning training for object detection based on said imagery data.
G01S 13/86 - Combinaisons de systèmes radar avec des systèmes autres que radar, p. ex. sonar, chercheur de direction
B63B 49/00 - Aménagements relatifs aux instruments nautiques ou d'aide à la navigation
G01S 13/06 - Systèmes déterminant les données relatives à la position d'une cible
G01S 13/88 - Radar ou systèmes analogues, spécialement adaptés pour des applications spécifiques
G01S 7/41 - Détails des systèmes correspondant aux groupes , , de systèmes selon le groupe utilisant l'analyse du signal d'écho pour la caractérisation de la cibleSignature de cibleSurface équivalente de cible
77.
Deployable emergency situation awareness support system
A deployable device mountable on a carrier vehicle and configured to collect situation awareness data. The deployable device includes at least one recorder device configured to collect situation awareness data. The deployable device is capable of being ejected from the carrier vehicle and can be configured to operate as a vehicle and/or be towed by the carrier vehicle. The deployable device can continue collection of situation awareness data after being ejected.
B64D 3/00 - Adaptations des aéronefs au remorquage ou à la prise en remorque
B64D 5/00 - Aéronefs transportés par un aéronef porteur, p. ex. pour être largués ou repris en vol
B64D 17/80 - Parachutes fonctionnant en conjonction avec l'aéronef, p. ex. pour le freinage de celui-ci
B64U 70/20 - Dispositions pour le lancement, le décollage ou l'atterrissage pour lancer ou capturer en vol les véhicules aériens sans pilote via un autre aéronef
An imaging method which comprises, while a line of sight of a camera is maintained fixedly oriented towards a target, controlling the camera to acquire an image by a sensor located at a current position relative to the camera, sending a command to an actuator of the sensor, for inducing a motion of the sensor relative to the camera along at least one direction, from the current position to a new position, controlling the camera to acquire an image by each of the pixel bands of the sensor, wherein motion of the sensor is performed during a first period of time, and the sensor is retained stationary at the new position during a second period of time, wherein acquisition of the image is performed during a third period of time, wherein a majority of the third period of time is within the second period of time.
H04N 23/695 - Commande de la direction de la caméra pour modifier le champ de vision, p. ex. par un panoramique, une inclinaison ou en fonction du suivi des objets
H04N 23/66 - Commande à distance de caméras ou de parties de caméra, p. ex. par des dispositifs de commande à distance
79.
SYSTEM AND METHOD FOR TRACKING AND CLASSIFYING MOVING OBJECTS
A system and method for tracking moving objects located within an area of interest are described. In operation, a sequence of periodic frames of the area of interest is generated from LiDAR measurements. The sequence includes preliminary periodic frames and periodic operational frames. Each periodic frame including point cloud data including static object data associated with static objects and dynamic object data associated with moving objects. The static data are filtered out by applying a pattern mask generated by using the predetermined number of the preliminary periodic frames. For each periodic operational frame, clusters of points related to the dynamic object data are generated. Tracks of the moving objects are provided. Each track is constructed from a plurality of clusters related to the same object. The plurality of clusters are obtained for a predetermined number of the periodic operational frames. Each cluster is defined by a corresponding characteristics vector associated with a corresponding moving object in a corresponding periodic operational frame. Each characteristics vector includes cluster parameters associated with the corresponding moving object.
There is provided a composite air vehicle system including: a first air vehicle capable of independent aerodynamic flight; a second air vehicle capable of independent aerodynamic flight; and at least one connector element configured for reversibly interconnecting the first air vehicle and the second air vehicle in tandem arrangement to provide a composite air vehicle capable of aerodynamic flight. The composite air vehicle system is configured for enabling at least in-flight separation of composite air vehicle into the first air vehicle and second air vehicle, and for enabling each one of the first air vehicle and said second air vehicle to operate independently of one another.
The presently disclosed subject matter includes a system and a method for launching a projectile towards a target, wherein the system comprises a control circuitry, a booster engine, and one or more thrusters adapted to be connected to the projectile and capable of being spun during launch around a longitudinal axis of the projectile, the control circuitry being operatively connected to the one or more thrusters; wherein responsive to ignition of propellant stowed in a combustion chamber of the booster engine, the booster engine causes the projectile to launch from its cell; following launch of the projectile, cause the projectile to turn at a certain rate and a certain azimuth.
F42B 10/66 - Pilotage par variation de l'intensité ou de la direction de la poussée
F41F 3/04 - Lanceurs de roquettes ou de torpilles pour roquettes
F41G 7/36 - Systèmes de commande de guidage pour missiles autopropulsés basés sur des données prédéterminées de la position de la cible utilisant des références inertielles
F42B 10/26 - Dispositions pour la stabilisation par rotation
82.
Cockpit of an airplane and method of operating an airplane
A cockpit for an airplane having, in a plan view, an aft direction, a central longitudinal axis parallel to the aft direction and a rear axis perpendicular to the central longitudinal axis. The cockpit as seen in the plan view comprises: a first seat having a first seating surface with a first seat rear edge passing through an intersection between the longitudinal and rear axes, the first seat being disposed within the cockpit and configured so as to allow a pilot sitting on the first seating surface to perform pre-determined primary pilot functions; and a second seat having a second seating surface with a second seat rear edge. The second seat has: an operational state, in which the second seat is disposed within the cockpit and configured so as to allow operational seating of a pilot on the second seating surface to perform pre-determined secondary pilot functions, the second seat rear edge being at an operational distance from the rear axis; and at least one non-operational state, in which the operational seating of the secondary pilot is disabled, the at least one non-operational state comprising a resting state in which the footprint of the second seat in plan view is longer in at least one dimension than the footprint of the second seat in the operational state, allowing a lying-down position of the secondary pilot.
There is provided a composite structure for an aerodynamic component having an aerofoil-like cross-section and a leading edge, the composite structure being in the form of a torsion box arrangement made from composite materials and having a core, the torsion box having a forward wall, an aft wall, a top wall and a bottom wall, together defining the core, the front wall being formed as the leading edge of the aerodynamic component. Also provided is a load-bearing composite structure for use with an aerodynamic component and configured for supporting at least one external load, this composite structure being made from composite materials and configured for being joined to the external aerodynamic surface of the aerodynamic component such as to be in overlying abutting relationship with at least a contact surface portion of the external aerodynamic surface, including the leading edge, at least a forward portion of each of the suction surface and the pressure surface thereof.
An air vehicle is provided including: a main lift generating wing arrangement having a port wing and a starboard wing, empennage and main propulsion system. The air vehicle further includes a distributed electrical propulsion (DEP) system having secondary electrical propulsion units coupled to each one of the port wing and the starboard wing. The main propulsion system is configured for providing sufficient thrust such as to enable powered aerodynamic flight of the air vehicle including at least: powered aerodynamic take off absent operation of the DEP system; and powered aerodynamic landing absent operation of the DEP system. The DEP system is configured for selectively providing at least augmented lift to the main lift generating wing arrangement in at least landing. A method for landing an air vehicle on a moving platform under separated wake conditions is also provided.
A variety of refueling devices, systems and methods are disclosed for use in in-flight refueling. In one example one such device is towed by a tanker aircraft via a fuel hose at least during in-flight refueling, and has a boom member with a boom axis. The boom member enables fuel to be transferred from the fuel hose to a receiver aircraft along the boom axis during in-flight refueling. The device maintains a desired non-zero angular disposition between the boom axis and a forward direction at least when the refueling device is towed by the tanker aircraft in the forward direction via the fuel hose.
B64D 39/04 - Adaptations de la structure des tuyauteries
B64D 3/00 - Adaptations des aéronefs au remorquage ou à la prise en remorque
G05D 1/00 - Commande de la position, du cap, de l'altitude ou de l'attitude des véhicules terrestres, aquatiques, aériens ou spatiaux, p. ex. utilisant des pilotes automatiques
G05D 1/10 - Commande de la position ou du cap dans les trois dimensions simultanément
86.
COMPOSITE MATERIAL WITH ENHANCED THERMAL CONDUCTIVITY AND METHOD FOR FABRICATION THEREOF
A composite member and a method for manufacturing polymeric material article are presented. The method comprising providing polymeric resin, providing selected amount of filler material, mixing filler material into the polymeric matrix to provide a polymeric filler mixture, compressing said polymeric filler mixture under pressure in the range of up to 350 bar, and curing said polymeric filler mixture to provide stable polymeric material. The resulting composite member is typically characterizes by having average filler to filler particle gap below 20 nm and substantially does not have air voids therein.
C09K 5/14 - Substances solides, p. ex. pulvérulentes ou granuleuses
C08J 3/21 - Formation de mélanges de polymères avec des additifs, p. ex. coloration en présence d'une phase liquide le polymère étant prémélangé avec une phase liquide
C08K 7/00 - Emploi d'ingrédients caractérisés par leur forme
There is provided a system and method of identifying a current location within a geographic region, the method comprising: obtaining, by a processor, a regional terrain model (RTM) comprising three or more vertical elevations indicative of a height of terrain in a respective cell of the geographic region; obtaining, for each of at least two reference terrain points, a 3D direction vector of the reference terrain point relative to the current location and an associated distance; and identifying a location in the geographic region as the current location in accordance with: the local area terrain elevation data, and the vertical elevations.
Aviation method comprising performing a single-pilot flight of inter-continental duration T>tp=predetermined single-pilot maximal single pilot flight duration; including using pilot-in-command logic empower a single airborne pilot to pilot via an airborne man-machine interface (MMI), only for a time window Wtp, while utilizing the human airborne pilot only for a time period W
B64C 13/18 - Dispositifs amorçant la mise en œuvre actionnés automatiquement, p. ex. répondant aux détecteurs de rafales utilisant un pilote automatique
B64C 13/20 - Dispositifs amorçant la mise en œuvre actionnés automatiquement, p. ex. répondant aux détecteurs de rafales utilisant des émissions de signaux
B64C 13/22 - Dispositifs amorçant la mise en œuvre actionnés automatiquement, p. ex. répondant aux détecteurs de rafales avec retour facile à la commande individuelle
G05D 1/00 - Commande de la position, du cap, de l'altitude ou de l'attitude des véhicules terrestres, aquatiques, aériens ou spatiaux, p. ex. utilisant des pilotes automatiques
A system for loading articles into a container is provided, comprising a platform unit and an elevator unit configured to adjust its elevation relative to the container and a platform unit comprising an opening facing the container and defining an edge of the platform unit, a transfer arrangement comprising a plurality of parallel independent transfer members defining a receiving surface and extending along a loading direction transverse to the edge and configured to move of the others, and a positioning arrangement to orient the article to a loading orientation on the receiving surface and position it at a predetermined loading position along an axis perpendicular to the loading direction. The transfer arrangement is configured to extend a subset of the transfer members in the loading direction through the opening, thereby facilitating placement of the article at a predetermined location within the container.
B65G 47/54 - Dispositifs pour transférer objets ou matériaux entre transporteurs, p. ex. pour décharger ou alimenter entre transporteurs se croisant l'un au moins étant du type à rouleaux
B64F 1/32 - Installations au sol ou installations pour ponts d'envol des porte-avions pour la manutention du fret
B65G 21/20 - Moyens incorporés ou fixés au châssis ou aux carters pour guider les porte-charges, les éléments de traction ou les charges portées sur les surfaces mobiles
91.
EVENT PREDICTION BASED ON MACHINE LEARNING AND ENGINEERING ANALYSIS TOOLS
A computerized system performs training of machine learning models to enable prediction of occurrence of event(s), which are associated with a system to be analyzed. The system performs the following: (a) provide trained Anomaly Detection Model(s). (b) provide Analysis Tool(s), configured to provide quantitative indications of the event(s). The quantitative indications of the event(s) are based on input events(s). (c) receive first unlabeled data associated with the system, where this data comprise sensor data, (d) input the first unlabeled data to the Anomaly Detection Model(s). (d) generate, using the Anomaly Detection Models, indications of occurrence of the input event(s), based on the first unlabeled data, (e) input the indications of the occurrence into the Tool(s). (f) generate, using the Tools, quantitative indications of the events, based the indications of the occurrence, (g) generate, using the quantitative indications, labels for the first unlabeled data.
According to the presently disclosed subject matter, it is suggested to use beacon signals as a navigational aid. More specifically, a platform equipped with a suitable communication antenna (e.g., beyond line of sight (BLOS) communication antenna) can search for a plurality of beacon signals, identify the signals, and determine the position of the platform using techniques such as triangulation.
G01S 5/02 - Localisation par coordination de plusieurs déterminations de direction ou de ligne de positionLocalisation par coordination de plusieurs déterminations de distance utilisant les ondes radioélectriques
There are provided examples of an enhanced cargo capacity aircraft, converted from a datum aircraft. The enhanced cargo capacity aircraft includes the datum aircraft and a cargo module. The datum aircraft includes at least a fuselage having a dorsal fuselage part. The cargo module is affixed to the datum aircraft, thereby converting the datum aircraft to the enhanced cargo capacity aircraft. The datum aircraft is designed for aerodynamic flight capability absent the cargo module. The enhanced cargo capacity aircraft is capable of aerodynamic flight. The cargo module provides enhanced cargo capacity to the datum aircraft. The cargo module includes an external aerodynamic fairing defining an internal cargo volume, and is configured for being conformally affixed in overlying relationship with respect to the dorsal fuselage part. The cargo module includes a cargo handling floor and at least one access door, and a cargo handling system configured for transporting and securing at least one cargo unit within the cargo volume. The cargo unit includes a standard unit load device (ULD).
Refueling devices for use in in-flight refueling operation are provided, including a body configured for being towed by a tanker aircraft and having a boom member that has a fuel delivery nozzle, a spatial control system and a longitudinal control system. The longitudinal displacement control system includes at least one panel element defining a front panel projected area orthogonal to a body longitudinal axis, each panel element being controllably and reversibly deployable incrementally to each one of a plurality of successive deployed positions between a fully retracted position and a fully deployed position, to provide a respective reversible incrementally increasing aft force to the refueling device at least during the in-flight refueling operation.
B64C 9/36 - Surfaces ou éléments de commande réglables, p. ex. gouvernes de direction repliables ou escamotables contre ou à l'intérieur d'autres surfaces ou d'autres éléments les éléments étant des fuselages ou des fuseaux moteurs
B64D 3/02 - Adaptations des aéronefs au remorquage ou à la prise en remorque pour remorquage de cibles
95.
Air vehicle and method of operation of air vehicle
An air vehicle has an airframe, aerodynamic lift-generating wings, and a propulsion system. The propulsion system provides propulsion to the air vehicle in powered aerodynamic flight mode and in vectored flight mode, and stability and control in vectored flight mode. The propulsion system includes a first set of non-pivotable first propulsion units, arranged in polygonal arrangement with respect to the airframe, enclosing the air vehicle center of gravity, providing a fixed vertical thrust vector and an aggregate vertical thrust sufficient for enabling vectored flight mode. The propulsion system includes a second set of pivotable second propulsion units, arranged in spaced relationship with respect to the center of gravity, and provide vectored control moments to the air vehicle in three rotational degrees of freedom. The second propulsion units enable angular displacement of the respective thrust vectors at least between a respective vertical position and a respective horizontal position, and provide at least an aggregate horizontal thrust sufficient for providing powered aerodynamic flight mode.
A wing system is provided for an air vehicle, the air vehicle having a fuselage including a fuselage longitudinal axis. The wing system includes a set of wings, configured for transitioning between a stowed configuration and a deployed configuration. The set of wings includes a first said wing having a first wing tip, a first wing longitudinal axis, and a first pivot axis; and a second said wing having a second wing tip, a second wing longitudinal axis, and a second pivot axis. The first pivot axis and the second pivot axis are non-coaxial. In the stowed configuration, the first wing and the second wing are in overlying relationship such that at least a majority of a pressure surface of one wing is facing a suction surface of the other wing, and the first wing tip is spaced from the second wing tip by a first lateral spacing. In the deployed configuration, the first wing is oriented with respect to the second wing such that the first wing tip is spaced from the second wing tip by a second lateral spacing greater than the first lateral spacing. The transitioning includes a pivoting operation, including: pivoting the first wing about the first pivot axis between the stowed configuration and the deployed configuration; and, pivoting the second wing about the second pivot axis between the stowed configuration and the deployed configuration.
A wing system is provided for an air vehicle, the air vehicle having a fuselage including a fuselage section and a fuselage longitudinal axis, the wing system having at least one wing deployment module. Each wing deployment module includes a set of wing elements, including at least a first wing element having a first wing element longitudinal axis, and a second wing element having a second wing element longitudinal axis. Each wing deployment module is configured for selectively transitioning between a respective stowed configuration and a respective deployed configuration. In the stowed configuration, the first wing element and the second wing element are in overlying relationship such that the first wing element longitudinal axis and the second wing element longitudinal axis are nominally parallel with one another. In the deployed configuration, the first wing element is oriented with respect to the second wing element such that the first wing element longitudinal axis is non-parallel with respect to the second wing element longitudinal axis.
A wing system is provided for an air vehicle, the wing system having a stowed configuration, a pre-deployed configuration, and a deployed configuration. The wing system includes two wings, each wing having aerofoil profiles and being pivotably deployable about a respective pivot axis between the pre-deployed configuration and the deployed configuration. In the stowed configuration the two wings are in first general superposed spatial relationship with respect to one another and are capable of being accommodated within an envelope having an envelope cross-sectional profile and a corresponding envelope cross-sectional area. In the pre-deployed configuration, the two wings are in second general superposed spatial relationship with respect to one another and capable of deploying to the deployed configuration. In the deployed configuration the wings are each capable of generating aerodynamic lift in an airstream. Each aerofoil profile of each wing is a slotted aerofoil having a primary element, a secondary element and a chord, the secondary element being pivotable with respect to the primary element and spaced therefrom by a gap. Each aerofoil profile has a respective maximum thickness, and a respective maximum absolute thickness. In the stowed configuration, the respective second element of each aerofoil of one wing is set at a different flap angle as compared with the respective second element of each aerofoil of the other wing.
There is provided a system for controlling at least first and second engines of an aircraft, comprising a common controlling unit configured to convert data representative of a thrust command transmitted by an actuating element controllable by a pilot or by an auto-throttle of the aircraft, into: (a) at least one first command usable by a controller of the first engine for controlling its operation based at least on said first command, and (b) at least one second command usable by a controller of the second engine for controlling its operation based at least on said second command, wherein said common controlling unit is operable to perform said conversion based at least on data representative of a level of operability of each engine, thereby making each engine to either comply with said thrust command or to operate differently from said thrust command, based at least on its level of operability.
B64D 31/10 - Dispositifs amorçant la mise en œuvre actionnés automatiquement en réponse à une défaillance des groupes moteurs pour empêcher une poussée asymétrique
B64D 31/04 - Dispositifs amorçant la mise en œuvre actionnés par l'homme
G05D 1/08 - Commande de l'attitude, c. à d. élimination ou réduction des effets du roulis, du tangage ou des embardées
A method of performing calibration of a target-positioning system of an Unmanned Aerial Vehicle (UAV) comprises: (a) receiving, from the system, measurement data, associated with calibration mission(s), and indicative of measurements recorded, by UAV sensor(s), at a first plurality of points. This data is indicative of coordinates of known-location target(s) (measured position information), (b) receiving known coordinates of these target(s) (known position information), (c) deriving correction data associated with each point, by comparing the measured and known position information. This enables correction of second measurement data associated with the sensor(s) and with a UAV target-location mission, in a situation of fixed sensor inaccuracies. This mission is associated with determining location information of other target(s). This data is indicative of measurements recorded by the sensor(s) at a second plurality of points. For corresponding points in the first and second pluralities of points, sensor orientations meet a first similarity criteria.
G01C 25/00 - Fabrication, étalonnage, nettoyage ou réparation des instruments ou des dispositifs mentionnés dans les autres groupes de la présente sous-classe
G06T 7/70 - Détermination de la position ou de l'orientation des objets ou des caméras
G01S 5/02 - Localisation par coordination de plusieurs déterminations de direction ou de ligne de positionLocalisation par coordination de plusieurs déterminations de distance utilisant les ondes radioélectriques
