An aircraft and a method of operating an aircraft. The aircraft includes a processor and an interface for receiving an input from an operator. The processor is configured to calculate an expected state of the aircraft for a selected flight plan of the aircraft, display the expected state for the flight plan, alter the expected state in response to the input from an operator, and operate the aircraft according to the altered state.
G01C 21/00 - Navigation; Instruments de navigation non prévus dans les groupes
G01C 23/00 - Instruments combinés indiquant plus d’une valeur de navigation, p.ex. pour l’aviation; Dispositifs de mesure combinés pour mesurer plusieurs variables du mouvement, p.ex. la distance, la vitesse ou l’accélération
G01S 13/94 - Radar ou systèmes analogues, spécialement adaptés pour des applications spécifiques pour éviter le sol
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. pilote automatique
2.
SYSTEMS AND METHODS FOR ASSESSING STRUCTURAL HEALTH
G01M 5/00 - Examen de l'élasticité des structures ou ouvrages, p.ex. fléchissement de ponts ou d'ailes d'avions
G06F 19/00 - Équipement ou méthodes de traitement de données ou de calcul numérique, spécialement adaptés à des applications spécifiques (spécialement adaptés à des fonctions spécifiques G06F 17/00;systèmes ou méthodes de traitement de données spécialement adaptés à des fins administratives, commerciales, financières, de gestion, de surveillance ou de prévision G06Q;informatique médicale G16H)
A fastener health monitoring system includes a structure including a first component and a second component, one or more fasteners securing the first component to the second component, and an optical fiber arranged adjacent to the one or more fasteners. The fiber is configured to detect strain on the structure from the one or more fasteners. Strain patterns are derivable from sensed data from the optical fiber, and any deviation in strain value greater than a threshold value at a particular fiber position along the optical fiber is indicative of a missing, damaged, or loosened fastener amongst the one or more of fasteners corresponding to that particular fiber position.
G01L 1/24 - Mesure des forces ou des contraintes, en général en mesurant les variations des propriétés optiques du matériau quand il est soumis à une contrainte, p.ex. par l'analyse des contraintes par photo-élasticité
A portable computerized device for an aircraft control system includes an input system for inputting commands, a device display for displaying information on the computerized device, a processor, a wireless communication module, and a non-transitory computer readable medium comprising computer executable instructions, the computer executable instructions configured to cause the processor to perform a method. The method can include detecting whether the portable computerized device is in a cockpit state such that the portable computerized device is in and/or docked to an aircraft cockpit or if the portable computerized device is in a remote state such that the portable computerized device is not in an aircraft cockpit or is not docked to an aircraft cockpit. If the portable computerized device is determined to be in a remote state, the method includes operating the remote device in a remote mode. If the portable computerized device is determined to be in a cockpit state, the method includes operating the device in a local mode.
A computer-implemented method and system for controlling an aircraft based on detecting and mitigating fatiguing conditions and aircraft damage conditions is disclosed. According to one example, a computer-implemented method includes detecting, by a processing system, a health condition of a component of the aircraft. The method further includes determining, by the processing system, whether the health condition is one of a fatigue condition or a damage condition. The method further includes implementing, by the processing system, a first action based at least in part on determining that the health condition is a fatigue condition to mitigate the fatigue condition. The method further includes implementing, by the processing system, a second action based at least in part on determining that the health condition is a damage condition to mitigate the damage condition.
G06F 17/00 - TRAITEMENT ÉLECTRIQUE DE DONNÉES NUMÉRIQUES Équipement ou méthodes de traitement de données ou de calcul numérique, spécialement adaptés à des fonctions spécifiques
H04N 5/33 - Transformation des rayonnements infrarouges
6.
ADAPTIVE CONTROL OF AIRCRAFT USING STRUCTURAL HEALTH MONITORING
A method for providing adaptive control to a fly-by-wire aircraft includes measuring via at least one first sensor a characteristic of at least one component of the aircraft and measuring via at least one second sensor a state of the aircraft. Using the characteristic of at least one component and the state of the aircraft, a determination of at least one of an actual damage and remaining life of the at least one component is made. The operational envelope of the aircraft is adapted based on the at least one of actual damage and remaining life of the at least one component. Adapting the operational envelope includes adjusting an outer boundary thereof to prohibit operation exceeding a safe operation threshold and generating an intermediate boundary of the operational envelope. Operation of the aircraft within the intermediate boundaries minimizes further damage accrual of the at least one component.
B64C 19/00 - Dispositifs de commande des aéronefs non prévus ailleurs
B64D 43/02 - Aménagements ou adaptations des instruments pour indiquer la vitesse des aéronefs ou les conditions de décrochage
B64D 45/00 - Indicateurs ou dispositifs de protection d'aéronefs, non prévus ailleurs
G01C 23/00 - Instruments combinés indiquant plus d’une valeur de navigation, p.ex. pour l’aviation; Dispositifs de mesure combinés pour mesurer plusieurs variables du mouvement, p.ex. la distance, la vitesse ou l’accélération
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. pilote automatique
G07C 5/08 - Enregistrement ou indication de données de marche autres que le temps de circulation, de fonctionnement, d'arrêt ou d'attente, avec ou sans enregistrement des temps de circulation, de fonctionnement, d'arrêt ou d'attente
A spherical bearing which extends from and connects to a deformable component includes an outer member and an inner member. The inner member is pivotable relative to the outer member about an axis. The inner member has an opening formed therein that defines a plurality of coplanar contact surfaces shaped to accommodate and contact the component. The plurality of contact surfaces are movable to accommodate deformation of the component positioned within the opening.
A gear train includes a first gear having teeth meshed with teeth of a second gear. Each tooth of the first gear includes a coast side and a drive side opposed to the coast side. The drive side has a pressure angle that is greater than that of the coast side. The gear train can be part of a powertrain system for a rotorcraft, and can replace a traditional gear train in a retrofit or new build. The first gear is a planet gear and the second gear is a ring gear wherein the planet gear and ring gear are in a planetary gear train configuration.
A gearbox includes a housing including a lubricant reservoir, at least one gear system arranged in the housing, at least one lubricant delivery passage operable to direct a flow of lubricant from a lubricant reservoir onto the at least one gear system, at least one lubricant return passage operable to guide the flow of lubricant to the lubricant reservoir, and a lubricant-out sensor fluidically connected to the at least one lubricant return passage. The lubricant-out sensor is operable to detect a non-pressure based parameter of the lubricant.
B64C 27/00 - Giravions; Rotors propres aux giravions
B64C 29/00 - Aéronefs capables d'atterrir ou de décoller à la verticale, p.ex. aéronefs à décollage et atterrissage verticaux [ADAV, en anglais VTOL]
F16N 29/00 - Dispositifs particuliers dans les installations ou systèmes de lubrification indiquant ou détectant des conditions indésirables; Utilisation des dispositifs sensibles à ces conditions dans les installations ou systèmes de lubrification
F16N 29/02 - Dispositifs particuliers dans les installations ou systèmes de lubrification indiquant ou détectant des conditions indésirables; Utilisation des dispositifs sensibles à ces conditions dans les installations ou systèmes de lubrification agissant sur l'alimentation en lubrifiant
F16N 29/04 - Dispositifs particuliers dans les installations ou systèmes de lubrification indiquant ou détectant des conditions indésirables; Utilisation des dispositifs sensibles à ces conditions dans les installations ou systèmes de lubrification permettant d'arrêter des pièces en mouvement
F16N 7/00 - Installations à huile ou autre lubrifiant non spécifié, à réservoir ou autre source portés par la machine ou l'organe machine à lubrifier
A water separator (108) includes a tube (112) defining a longitudinal axis, wherein the tube (112) includes a tube wall separating an interior (114) of the tube from an exterior (116) thereof. A tube insert (118) is mounted within the tube (112). The tube insert (118) includes a sheet (119) that is helically twisted about the longitudinal axis. An environmental control system (100) includes an air conditioner (102) with a discharge duct (104) for providing cooled air to an air conditioned space. A water separator (108) as described above is connected in line with the discharge duct (104) for passage of cooled air therethrough.
B64D 13/00 - Aménagements ou adaptations des appareils de conditionnement d'air pour équipages d'aéronefs, passagers ou pour emplacement réservé au fret
B64D 13/06 - Aménagements ou adaptations des appareils de conditionnement d'air pour équipages d'aéronefs, passagers ou pour emplacement réservé au fret l'air étant climatisé
A rotor blade deflection sensing system including a rotor blade having a first surface, a second surface, a third surface and a fourth surface. At least two fiber optic sensor arrays are mounted to the rotor blade. At least one of the at least two fiber optic sensor arrays is mounted to one of the first surface, the second surface, the third surface and the fourth surface and another of the at least two fiber optic sensor arrays being mounted to another of the first surface, a second surface, a third surface and a fourth surface. A controller is operatively connected to the at least two fiber optic sensor arrays. The controller determines one or more of a flapwise and an edgewise displacement based on inputs from the at least two fiber optic sensor arrays.
A tail rotor blade for a helicopter includes a blade body defining a longitudinally extending spar cavity, a leading edge forward of the spar cavity, and a trailing edge aft of the spar cavity. Upper and lower airfoil surfaces extend from the leading edge to the trailing edge on opposite sides of the spar cavity. The upper and lower airfoil surfaces define between one another a constant airfoil segment and transition airfoil segments disposed longitudinally adjacent to the constant airfoil segment on inboard and outboard sides of the constant airfoil segment.
A herringbone gear includes a cylindrical body having a circumferential face having a width. A first helical gear tooth on the circumferential face has a first configuration, a second helical gear tooth on the circumferential face has a second configuration, and a transition on the circumferential face extends between the first helical gear tooth and the second helical gear tooth. An involute form taken within a transverse plane of the circumferential face remains constant over the width.
B23F 7/00 - Fabrication de dents d'engrenage à chevrons
B23H 9/00 - Usinage spécialement conçu pour le traitement d'objets métalliques particuliers ou pour obtenir des effets ou des résultats particuliers sur des objets métalliques
B23P 15/14 - Fabrication d'objets déterminés par des opérations non couvertes par une seule autre sous-classe ou un groupe de la présente sous-classe de pièces d'engrenage, p.ex. de pignons
F16H 1/08 - Transmissions à engrenages pour transmettre un mouvement rotatif sans engrenages à mouvement orbital comportant uniquement deux organes engrenés dont les axes sont parallèles les organes ayant des dents en hélice, en chevrons ou similaires
A fairing system, includes a hub fairing and a fixed fairing, such as a shaft fairing or a pylon fairing, both arranged about a rotation axis. A gap is defined between the hub fairing and the fixed fairing, and a seal assembly is axially interposed between the hub fairing and the fixed fairing. The fixed fairing and the hub fairing are both removably mounted to the seal assembly such that either or both of the fairings can be dismounted from the seal assembly without disturbing the seal assembly to provide access to components disposed within the fairing.
A blade includes an elongated body having a leading edge, a trailing edge, a root end, and a tip end, a fluid inlet arranged closer to the root end than the fluid outlet, a fluid outlet arranged near the tip end of the elongated body, and a centrifugal air flow channel defined within the body between the inlet and the outlet to direct air from the inlet to the outlet to issue the flow when the rotor blade is rotating in a rotational path. The blade also includes a valve to selectively open and close the centrifugal air flow channel to selectively issue the flow and change a blade vortex issuing from the rotor blade at discrete portions of the rotational path of the rotor blade. A controller can be operatively connected to the valve to control the valve to open and close the centrifugal air flow channel.
A vibration control assembly for an aircraft includes a housing operatively coupled to the aircraft. Also included is a cage disposed within an interior region of the housing, the cage rotatable within the housing about a first axis. Further included is a gyroscope wheel disposed within the cage and rotatable about a second axis other than the first axis, wherein a controllable moment is imposed on the aircraft upon rotation of the gyroscope wheel to counter vibratory moments produced by the vehicle. Yet further included is a control assembly at least partially surrounding the gyroscope wheel for controlling the controllable moment. The control assembly includes a structure having an inner surface, a track disposed along the inner surface, and an arm operatively coupled to the gyroscope wheel, the arm having an end disposed within the track, the gyroscope wheel angularly displaceable upon translation of the arm along the track
A method for controlling deployment of an airbag relative to ground contact includes retrieving a predicted ground contact time for an aircraft from a crash prediction module, retrieving seat position measurements and occupant data for a seat in the aircraft, and comparing the predicted ground contact time, the seat position measurements and the occupant data to pre-established data to determine a custom airbag deployment time with respect to the predicted ground contact time, for at least one airbag on the aircraft. The method includes sending a signal to deploy the at least one airbag based on the custom airbag deployment time.
B60R 21/015 - Circuits électriques pour déclencher le fonctionnement des dispositions de sécurité en cas d'accident, ou d'accident imminent, de véhicule comportant des moyens pour détecter la présence ou la position des passagers, des sièges des passagers ou des sièges pour enfants, p.ex. pour mettre hors service le déclenchement
B60R 21/01 - Circuits électriques pour déclencher le fonctionnement des dispositions de sécurité en cas d'accident, ou d'accident imminent, de véhicule
G05D 3/00 - Commande de la position ou de la direction
A drive system for a rotorcraft includes at least one engine, the engine including a compressor section, and a turbine section positioned rearward from the compressor section. A main rotor input shaft extends from a rotor power turbine of the turbine section and is connectable to a main rotor assembly of the rotorcraft to transfer rotational energy from the rotor power turbine to the main rotor assembly. An auxiliary input shaft extends from an auxiliary power turbine of the turbine section and is connectible to an auxiliary rotor assembly of the rotorcraft to transfer rotational energy from the auxiliary power turbine to the auxiliary rotor assembly.
B64C 27/14 - Entraînement direct entre groupe propulseur et moyeu du rotor
F02C 7/36 - Transmission de puissance entre les différents arbres de l'ensemble fonctionnel de turbine à gaz, ou entre ce dernier et l'utilisateur de puissance
A closeout structure for a rotor blade includes a first fluid channel for supplying a first pressure to a first port of a trailing edge (TE) device, a second fluid channel for supplying a second pressure to a second port of the TE de vice, and a trough disposed between the first fluid channel and the second fluid channel. The closeout structure forms a double- W shape.
B64C 27/54 - Mécanismes pour la commande du réglage ou du mouvement de la pale par rapport à la tête du rotor, p.ex. mouvement de traînée
B64C 27/59 - Transmissions, p.ex. en liaison avec les moyens déclenchant ou agissant sur les pales mécaniques
B64C 27/64 - Transmissions, p.ex. en liaison avec les moyens déclenchant ou agissant sur les pales utilisant la pression d'un fluide, p.ex. avec un amplificateur de puissance à fluide
An exhaust cooling arrangement includes a first duct having a first inlet and a first outlet, a fairing positioned radially outwardly of the first duct defining an annular space between the fairing and the first duct, and a second duct having a second inlet and a second outlet, the second inlet being positioned upstream of the first outlet within the annular space such that fluid within the annular space can flow along an inside surface of a wall defining the second duct and an outside surface of the wall, upstream being defined by a direction of fluid flow through the annular space.
A box frame hub arm structure is provided and includes a body having an outboard surface, which is disposable to abut with an inboard surface of an outboard arm of an aircraft rotor head, and lead/lag sides. The body is formed to define a first cavity, an aperture communicative with the first cavity through the outboard surface and second and third cavities. The second and third cavities extend outwardly in opposite lead/lag directions from the first cavity to the lead/lag sides.
A flexbeam rotor blade assembly includes a flexbeam having a body that includes a first surface, a second, opposing surface, and an opening extending through the first and second surfaces. At least one snubber is mounted to one of the first and second surfaces spaced along the body from the opening. A snubber retainer is mounted to one of the first and second surfaces between the body and the at least one snubber. The snubber retainer includes a retainer plate having a snubber attachment member to which the snubber assembly is mounted and a mounting arm including a retainer plate opening spaced from the snubber attachment member. The retainer plate opening registers with the opening in the flexbeam. A mechanical fastener extends through the retainer plate opening and the opening in the flexbeam. The mechanical fastener joins the snubber retainer to the one of the first and second surfaces.
A protective cover is disclosed for teeth of a gear body. The protective cover includes a desiccant disposed in a polymer enclosure. A method of protecting a gear is disclosed. The method involves generating a digital model of a protective cover having a surface portion that matches a surface contour of the gear teeth and inputting the digital model into an additive manufacturing apparatus or system. A protective cover is formed by repeatedly applying energy from an energy source to fuse successively applied incremental quantities of a polymer corresponding to the digital model of the protective cover, and the gear teeth are covered with the surface portion of the protective cover that matches the surface contour of the gear teeth.
B23F 17/00 - Méthodes ou machines particulières pour la fabrication de dents d'engrenage, non couvertes par les groupes
B65D 6/00 - Réceptacles dont le corps est formé par jonction ou liaison de plusieurs composants rigides ou sensiblement rigides, constitués en totalité ou principalement en métal, en matière plastique, en bois ou en un matériau de remplacement
B65D 8/00 - Réceptacles de section transversale courbe, dont le corps est formé par jonction ou liaison de plusieurs composants rigides, ou sensiblement rigides, constitués en totalité ou principalement en métal, en matière plastique, en bois ou en un matériau d
A system, method, and computer program for detecting and isolating structural faults is provided. To detect and isolate structural faults, a plurality of sensed features that corresponds to sensor data from the monitoring sub-system and a plurality of estimated features that corresponds to the plurality of sensed features can be generated. Further, the plurality of sensed features and the plurality of estimated features can be compared to produce a plurality of residuals. From the plurality of residuals, at least one structural fault within the vehicle are determined and isolated for further use of maintenance decision support.
G01B 5/28 - Dispositions pour la mesure caractérisées par l'utilisation de techniques mécaniques pour mesurer la rugosité ou l'irrégularité des surfaces
A gearbox system includes a first drive gear rotatable about an axis of rotation and a second drive gear disposed coaxial with the first drive gear and rotatable about the axis of rotation. An input shaft provides a first torque and includes an input gear. Driving pinions are operably connected to the input gear and positioned between the first drive gear and the second drive gear compliantly along a direction parallel to the axis of rotation. Each driving pinion drives the first drive gear in a first direction about the axis of rotation and drives the second drive gear in a second direction opposite the first direction about the axis of rotation. Each driving pinion transfers an equal second torque to the first drive gear and the second drive gear.
An inset configured for use in a rotor blade is provided including a body having a shape generally complementary to a hole formed in the rotor blade. An opening extends between a first surface and a second surface of the body. The opening is configured to provide a fluid flow path between an interior and an exterior of the rotor blade.
A device for altering infrared signature of an exhaust duct includes a housing configured to attach to an exhaust duct of a vehicle and at least one body attached to the housing at opposing ends of the at least one body, an opening in at least one of the opposing ends being in fluidic communication with a cavity within the at least one body such that fluid can flow into the cavity through the opening.
A method for diagnosing the function of an anti-ice/start bleed valve (AISBV) includes determining an operating mode of an engine and retrieving current engine system data associated with the operating mode. The method includes indicating whether the AISBV is functioning properly based on the current engine system data. An AISBV assessment system includes an AISB V assessment module configured to be operatively connected to a plurality of sensors. The AISBV assessment module includes a processor operatively connected to a memory, wherein the memory includes instructions recorded thereon that, when read by the processor, cause the processor to determine an operating mode of an engine, retrieve current engine system data associated with the operating mode, and indicate whether an AISBV is functioning properly based on the current engine system data.
A system and method are provided to perform loads-based structural health monitoring (LBSHM) of a dynamical system. The method includes receiving, by at least one computer, sensing data responsive to sensing at least one of a parametricai state and a response of the dynamical system, and determining a Koopman mode and a Koopman eigenvalue. The Koopman mode represents a correlation between the sensor data output by the plurality of sensors. The Koopman eigenvalue represents a frequency component associated with the sensor data and growth or decay of energy associated with the sensor data. The method further includes generating, by the at least one computer, an estimation model to determine a linear estimation based on the Koopman mode and the Koopman eigenvalue that estimates a load response of the dynamical system based on growth or decay of energy associated with the sensor data.
G01H 1/00 - Mesure des vibrations dans des solides en utilisant la conduction directe au détecteur
G01H 1/12 - Mesure des vibrations dans des solides en utilisant la conduction directe au détecteur les vibrations étant longitudinales ou non spécifiées
G01H 11/08 - Mesure des vibrations mécaniques ou des ondes ultrasonores, sonores ou infrasonores par détection des changements dans les propriétés électriques ou magnétiques par des moyens électriques utilisant des dispositifs piézo-électriques
G01M 99/00 - Matière non prévue dans les autres groupes de la présente sous-classe
G01N 29/14 - Recherche ou analyse des matériaux par l'emploi d'ondes ultrasonores, sonores ou infrasonores; Visualisation de l'intérieur d'objets par transmission d'ondes ultrasonores ou sonores à travers l'objet utilisant des techniques d'émission acoustique
A computer system and method is provided to filter clearance sensor data output by a sensor system during a load/offload procedure of a first object relative to a second object. A processing device of the computer system is configured to access hard threshold data, unique threshold data, and sensor data output by the sensor system sensing aspects of the load/offload procedure. The processing device is further configured to determine whether the sensor data exceeds the unique threshold, determine whether the sensor data that is determined to exceed the unique threshold is voidable data related to a noncritical event, and generate filtered sensor data that includes modifications to the voidable data.
B60R 21/00 - Dispositions ou équipements sur les véhicules pour protéger les occupants ou les piétons ou pour leur éviter des blessures en cas d'accidents ou d'autres incidents dus à la circulation
B60R 25/10 - VÉHICULES, ÉQUIPEMENTS OU PARTIES DE VÉHICULES, NON PRÉVUS AILLEURS Équipements ou systèmes pour interdire ou signaler l’usage non autorisé ou le vol de véhicules actionnant un dispositif d’alarme
B60W 30/00 - Fonctions des systèmes d'aide à la conduite des véhicules routiers non liées à la commande d'un sous-ensemble particulier, p.ex. de systèmes comportant la commande conjuguée de plusieurs sous-ensembles du véhicule
G01C 21/00 - Navigation; Instruments de navigation non prévus dans les groupes
A blade includes a blade body having a surface and a hole extending through the surface of the blade body. The hole defines a hole axis and a plane perpendicular to the hole axis. The hole has an elongated hole perimeter within the plane. The hole perimeter includes a plurality of non-linear perimeter sections to minimize stress concentration around the elongated hole perimeter while maximizing the usable opening area. A rotor system includes a rotor hub and a blade as recited above. The blade extends radially outward from the rotor hub. The blade defines a root end proximate to the rotor hub, a tip end opposite the root end.
A fuel vent connector includes a longitudinal axis and a flow path along the longitudinal axis. The connector further includes a first portion pivotally supporting a plurality of fingers, each finger amongst the plurality of fingers having a latching head biased radially outwardly and configured to latch within a fuel vent opening. The connector further includes a second portion biased longitudinally away from the first portion with respect to the longitudinal axis. The flow path extends through the first and second portions, and longitudinal movement of the second portion towards the first portion moves the fingers radially inward.
B60K 15/035 - Réservoirs de carburant caractérisés par de moyens d'aération
F16L 37/127 - Accouplements du type à action rapide dans lesquels l'assemblage entre les extrémités s'aboutant ou se chevauchant est maintenu par des organes de blocage utilisant des crochets, cliquet, ou autres organes de blocage mobiles ou que l'on peut insérer utilisant des crochets articulés autour d'un axe
F16L 37/138 - Accouplements du type à action rapide dans lesquels l'assemblage entre les extrémités s'aboutant ou se chevauchant est maintenu par des organes de blocage utilisant des crochets, cliquet, ou autres organes de blocage mobiles ou que l'on peut insérer utilisant un manchon mobile axialement
A method of providing cyber security for a vehicle includes monitoring, by a cyber security system of the vehicle, a plurality of parameters acquired from at least one communication bus of the vehicle. The parameters are filtered to identify parameters of interest for cyber security threat detection. An evaluation of the parameters of interest is performed with respect to one or more of normal conditions and abnormal conditions to identify at least one likely cyber security threat in the vehicle based on identifying at least one condition that does not match the normal conditions or at least one condition that does match the abnormal conditions. One or more recovery actions are triggered based on identifying the at least one likely cyber security threat in the vehicle.
A gearbox is provided having a housing, a gear having a plurality of teeth operationally configured within the housing, and a laser peening device located within the housing and configured to perform active laser peening on a predetermined surface of the gear while the gear is rotated within the housing. A method of maintaining compressive residual stresses in a gear is provided, the method including operating a gearbox to rotate a gear within the gearbox and laser peening a predetermined surface of the gear with a laser peening device located within the gearbox.
A vibratory weight-on-wheels (WOW) sensing system is provided for use with aircraft landing gear and a wheel coupled to the aircraft landing gear. The WOW sensing system includes a vibration sensor disposed proximate to the wheel and configured to sense vibratory characteristics of a component of the aircraft landing gear and to issue a sensing reflective signal and a processing unit disposed in signal communication with the vibration sensor such that the processing unit is receptive of the sensing reflective signal. The processing unit is configured to analyze the sensing reflective signal to thereby identify that a landing condition is in effect.
F16F 7/10 - Amortisseurs de vibrations; Amortisseurs de chocs utilisant un effet d'inertie
B60G 17/018 - Suspensions élastiques permettant d'ajuster les caractéristiques des ressorts ou des amortisseurs de vibrations, de réguler la distance entre la surface porteuse et la partie suspendue du véhicule ou de bloquer la suspension pendant l'utilisation pou les moyens de régulation comportant des éléments électriques ou électroniques caractérisés par l'utilisation d'un mode de traitement du signal ou d'une méthode de commande spécifiques
F16F 15/02 - Suppression des vibrations dans les systèmes non rotatifs, p.ex. dans des systèmes alternatifs; Suppression des vibrations dans les systèmes rotatifs par l'utilisation d'organes ne se déplaçant pas avec le système rotatif
G05D 19/02 - Commande des oscillations mécaniques, p.ex. de l'amplitude, de la fréquence, de la phase caractérisée par l'utilisation de moyens électriques
A bearing arrangement for use with a structure defining an outer surface which expands and contracts inward and outward relative to the structure includes, a member having at least one inner surface to face the outer surface, and at least one protrusion extending from the inner surface, the at least one protrusion being biased toward and in contact with the outer surface and maintains contact as the structure expands and contracts.
B64C 27/605 - Transmissions, p.ex. en liaison avec les moyens déclenchant ou agissant sur les pales mécaniques comportant un plateau oscillant, des mécanismes à tringlerie ou à came
B64C 27/54 - Mécanismes pour la commande du réglage ou du mouvement de la pale par rapport à la tête du rotor, p.ex. mouvement de traînée
B64C 27/58 - Transmissions, p.ex. en liaison avec les moyens déclenchant ou agissant sur les pales
F16C 27/00 - Paliers ou supports de paliers élastiques ou extensibles pour mouvement de rotation exclusivement
F16C 27/08 - Paliers ou supports de paliers élastiques ou extensibles pour mouvement de rotation exclusivement pour charges axiales principalement, p.ex. pour arbres disposés verticalement
A vibration damping device is configured to reduce vibration that causes lateral flexing of an elongated member that extends along a centerline. The device includes a split sleeve co-extending with and disposed about the elongated member, and a spring that extends about the sleeve and exerts a force that biases the sleeve radially inward.
F16F 15/10 - Suppression des vibrations dans les systèmes rotatifs par utilisation d'organes mobiles avec le système lui-même
F16C 27/00 - Paliers ou supports de paliers élastiques ou extensibles pour mouvement de rotation exclusivement
F16F 15/12 - Suppression des vibrations dans les systèmes rotatifs par utilisation d'organes mobiles avec le système lui-même utilisant des organes élastiques ou des organes amortisseurs de friction, p.ex. entre un arbre en rotation et une masse giratoire montée dessus
F16F 15/121 - Suppression des vibrations dans les systèmes rotatifs par utilisation d'organes mobiles avec le système lui-même utilisant des organes élastiques ou des organes amortisseurs de friction, p.ex. entre un arbre en rotation et une masse giratoire montée dessus utilisant des ressorts comme organes élastiques, p.ex. des ressorts métalliques
A lubrication system for a transmission includes a flow-metering device and a controller. The controller is operatively associated with the f!ow-metering device to cause the flow-metering device to intermittently issue lubricant from the flow-metering device into a transmission based on an operating parameter of the transmission.
A piezoelectric sensor assembly for measuring a force quantity on a structure includes at least one piezoelectric sensor, each including an element and two electrodes each projecting outward from the element. An electronic processor of the assembly is configured to receive data from the sensor, wherein the data includes a voltage with a magnitude that is indicative of a dynamic load (i.e., amplitude modulation mode) placed upon the structure. The processor may be configured to interrogate the piezoelectric sensor for its resonant frequency change which is indicative of the load applied to the structure at low operation frequency and to which the piezoelectric sensor would not otherwise respond well. The dual mode operation of the piezoelectric sensor extends the frequency range of the strain measurement from the dynamic range to static or quasi-static range.
A method for diagnosing leaks in a hydraulic accumulator includes measuring the time required to discharge the hydraulic accumulator to determine an actual discharge duration. The method includes comparing the actual discharge duration to an expected discharge duration to generate a condition indicator. The condition indicator correlates to the presence or absence of a leak.
A method of locating position on a component includes engaging a template with a component and marking a location on the component using marking features of the template. Marking a location can include marking a plurality of locations on the component using a plurality of respective marking features of the template. Each marking feature of the template can include a corner formed where at least two edges meet on the template. Marking each respective location on the component can include marking two line segments that cross at an intersection point, wherein the two line segments follow the edges of the template at each respective corner, to mark the respective location on the component at the intersection of the two respective line segments. For example, marking each location can include marking a center point location for a strain gage, as well as the horizontal and vertical orientation.
A structural reinforcement member is provided to be affixable to a metallic member. The metallic member defines a stress concentration section at which the metallic member is subject to loading in at least one direction such that stress is generated at the stress concentration section in at least one corresponding principal stress direction. The structural reinforcement member includes a polymer matrix composite (PMC) patch element and a bondline. The PMC patch element includes fibers suspended within a polymer matrix. The bondline is disposed to affix the PMC patch element to a surface of the metallic member at the stress concentration section such that the fibers extend along the principal stress direction.
B32B 15/08 - Produits stratifiés composés essentiellement de métal comprenant un métal comme seul composant ou comme composant principal d'une couche adjacente à une autre couche d'une substance spécifique de résine synthétique
B32B 37/22 - Procédés ou dispositifs pour la stratification, p.ex. par polymérisation ou par liaison à l'aide d'ultrasons caractérisés par les propriétés des couches toutes les couches existant et présentant une cohésion avant la stratification impliquant l'assemblage à la fois de couches individualisées et de couches continues
E04B 1/24 - Structures comportant des éléments porteurs allongés, p.ex. colonnes, poutres, ossatures les pièces porteuses étant métalliques
E04C 3/29 - Poutrelles; Solives, fermes ou structures analogues à des fermes, p.ex. préfabriquées; Linteaux; Traverses formés d'éléments de différents matériaux
E04C 3/36 - Colonnes; Piliers; Arcs-boutants constitués d’une combinaison de plusieurs matériaux
43.
CONTROL SYSTEM FOR ROTORCRAFT IN-FLIGHT ENGINE RESTARTING
A control system for an in-flight engine restart system of a rotorcraft includes an engine control unit that controls and detects status of an engine. The control system also includes a flight control computer that communicates with the engine control unit, an engine operation control system, and a pilot interface including pilot controls. The engine operation control system includes a processor that initiates a health check of the in-flight engine restart system to determine an in-flight engine restart system status. The engine operation control system processes engine mode of operation commands to establish an engine mode of operation, and delivers commands to aspects of the in-flight engine restart system including the engine control unit based on processing of the engine mode of operation commands. The engine operation control system reports the in-flight engine restart system status and results of the engine mode of operation commands to the flight control computer.
A clearance sensor system is provided for use in moving first and second articles and includes a driving element disposed to drive and manipulate the first article relative to the second article, a plurality of sensors arrayed about at least the second article to generate real-time readings of physical separation of the first and second articles and a controller operably coupled to the driving element and the plurality of sensors. The controller is configured to facilitate an execution of real-time or quasi-dynamic control of a driving of the first article by the driving element in accordance with the readings of the physical separation between the first and second articles provided by the plurality of sensors, and a post-processing of data relating to the real-time or quasi-dynamic control of the driving and the manipulation of the first article by the driving element.
A unitary core panel for a composite sandwich structure includes a plurality of cell walls defining a plurality of core cells, the plurality of cell walls extending across a thickness of the core, the plurality of core cells including one or more defined structural nonuniformities resulting in nonuniform properties of the core panel. A method of forming a core panel for a composite sandwich structure includes determining structural requirements of the core panel, designing the core panel to satisfy the structural requirements with one or more local nonuniformities in the core panel, and manufacturing the core panel as a unitary core panel with the one or more local nonuniformities.
B32B 3/08 - Caractérisés par des caractéristiques de forme en des endroits déterminés, p.ex. au voisinage des bords caractérisés par des éléments ajoutés à des endroits déterminés
B32B 3/12 - Produits stratifiés caractérisés essentiellement par le fait qu'une des couches comporte des discontinuités ou des rugosités externes ou internes, ou bien qu'une des couches est de forme générale non plane; Produits stratifiés caractérisés essentiellement par des particularismes de 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
B33Y 80/00 - Produits obtenus par fabrication additive
F16B 5/01 - Jonction de feuilles ou de plaques soit entre elles soit à des bandes ou barres parallèles à elles par organes de fixation spécialement adaptés pour panneaux en nid d'abeilles
B64C 1/12 - Structure ou fixation de panneaux de revêtement
46.
ADAPTIVE LANDING GEAR ASSEMBLY FOR ROTARY WING AIRCRAFT
An adaptive landing gear assembly for a rotary wing aircraft, the adaptive landing gear assembly including a controller; a first landing gear support having a first ground contact element; and a second landing gear support having a second ground contact element; the controller independently controlling the first landing gear support and the second landing gear support.
A fairing for a landing gear wheel assembly on a tail sitter aircraft is disclosed, which includes a fairing housing defining a longitudinal axis, and at least one pair of laterally opposed aerodynamic tail surfaces extending radially outward from the fairing housing for added flight stability.
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
A seat base assembly for a wheelchair includes a dock configured to be mounted to a vehicle frame. An attenuating mechanism is operatively connected to the dock to absorb impact between the vehicle frame and a wheelchair. An interface assembly is operatively connected to the attenuating mechanism to connect a wheelchair to the attenuating mechanism. A crashworthy wheelchair includes a seat having arm rests and a seat back extending therefrom. Front wheels and back wheels are operatively connected to the seat. Each arm rest includes a downward opening slot configured to accommodate a respective one of the back wheels during a negative G event. The wheelchair can include a hook extending down ward from the seat to engage with a respective mating portion of the seat base assembly.
A Transistor Resonant Characteristic Sensor (TReCS) includes a sensing element positioned along electronic equipment so that the sensing element is electromagnetic ally coupled to the electronic equipment. The sensing element includes a coil. The sensing element is configured to detect magnetic oscillations associated with a characteristic signal generated by the electronic equipment. The TReCS sensor further includes an evaluation circuit connected to the sensing element for monitoring health state of the electronic equipment. The evaluation circuit includes one or more processing elements configured to diagnose health state of the electronic equipment based on extracted baseband information associated with the characteristic signal.
G01D 3/08 - Dispositions pour la mesure prévues pour les objets particuliers indiqués dans les sous-groupes du présent groupe avec dispositions pour protéger l'appareil, p.ex. contre les fonctionnements anormaux, contre les pannes
G01D 5/12 - Moyens mécaniques pour le transfert de la grandeur de sortie d'un organe sensible; Moyens pour convertir la grandeur de sortie d'un organe sensible en une autre variable, lorsque la forme ou la nature de l'organe sensible n'imposent pas un moyen de conversion déterminé; Transducteurs non spécialement adaptés à une variable particulière utilisant des moyens électriques ou magnétiques
50.
AERIAL VEHICLE INCLUDING AUTONOMOUS ROTOR SPEED CONTROL
A rotary aerial vehicle (AV) includes an engine configured to rotate at least one rotor at a variable rotor speed, a full authority electronic microcontroller (FAEM) in electrical communication with the engine. The FAEM is configured to output at least one electronic engine control signal that controls operation of the engine. An electronic rotor speed microcontroller (ERSM) is in electrical communication with the FAEM, and the ERSM is configured to dynamically determine at least one mission objective of the rotary AV, and outputs an electronic rotor speed control signal that commands the FAEM to adjust the rotor speed of the at least one rotor.
An aircraft is provided and includes an airframe, a main rotor assembly operably disposed at an upper portion of the airframe to provide lift, a propulsor assembly operably disposed at a tail portion of the airframe to provide thrust and a control system. The control system includes a mono-cyclic swashplate assembly that is translatable in a translation direction to execute collective control of the propulsor assembly and rotatable about an axis defined transversely with respect to the translation direction to execute cyclic control of the propulsor assembly.
B64C 27/605 - Transmissions, p.ex. en liaison avec les moyens déclenchant ou agissant sur les pales mécaniques comportant un plateau oscillant, des mécanismes à tringlerie ou à came
52.
METHOD FOR PREDICTING CORROSION POTENTIAL, MONITORING CONTAMINANT LOAD AND OPTIMIZING CORROSION MAINTENANCE
A corrosion management method is provided and includes storing an asset fleet at a location, generating a corrosion rate stressor by reference to models for any component of an asset of the asset fleet corresponding to the location and storage practice of the asset, predicting an accumulated corrosion stressor severity from the generated corrosion rate stressor, measuring an actual corrosion rate stressor at the location and revising the models in accordance with a difference between the predicted accumulated corrosion stressor severity and the measured actual corrosion rate stressor.
According to one embodiment of the disclosure, a knob to latch interface includes a body, a latch in operable communication with the body movable between a latched position and an unlatched position, and a knob longitudinally positionable between a first position and a second position relative to the body and in operable communication with the latch, an outer radial extent of the knob being operationally engagable only while in one of the first position and the second position.
E05C 1/14 - Dispositifs d'immobilisation avec pênes se déplaçant de façon rectiligne avec action d'une clenche avec poignée de manœuvre ou organe équivalent se déplaçant autrement que rigidement avec la clenche dont la poignée ou organe se déplace essentiellement vers le ou à l'encontre du, plan du battant ou du dormant
A tension torsion strap by which a blade is connectable with a hub of a propulsor is provided. The tension torsion strap includes an elongate body formed to define attachment features at opposite ends thereof, the attachment features being connectable to the blade at one of the opposite ends and to the hub at the other of the opposite ends, fibrous materials extending along the elongate body and around the attachment features and pretension flanges elastically interposable between the hub and the elongate body. The pretension flanges are configured to maintain pretension in the fibrous materials above a predefined pretension level when the attachment features are connected to the blade and the hub.
A method of assessing airframe corrosion risk includes determining a component corrosion stress based on data from at least one of a corrosivity sensor, an aircraft exposure history, a climate database, or an aircraft configuration. The method includes generating a component corrosion risk based on the determined component corrosion stress. An accumulated component corrosion risk is calculated based on the component corrosion risk and a historical component corrosion risk. An airframe corrosion risk is determined based on the accumulated component corrosion risk.
G01N 21/95 - Recherche de la présence de criques, de défauts ou de souillures caractérisée par le matériau ou la forme de l'objet à analyser
G06F 17/40 - Acquisition et consignation de données
G06Q 90/00 - Systèmes ou méthodes spécialement adaptés à des fins administratives, commerciales, financières, de gestion ou de surveillance, n'impliquant pas de traitement significatif de données
56.
SYSTEMS AND METHODS FOR ASSESSING CONDITION OF A SENSOR
A method for assessing the condition of a sensor includes applying a diagnostic signal to the sensor using a controller and receiving a dynamic output response. The dynamic output response includes a voltage transient and return to a baseline sensor output voltage. The dynamic output response is thereafter compared to a reference output response, and condition of the sensor is indicated as unreliable if the dynamic output response differs from the reference output response by a predetermined amount for a dynamic output response output parameter.
G01R 31/28 - Test de circuits électroniques, p.ex. à l'aide d'un traceur de signaux
G01L 25/00 - Test ou étalonnage des appareils pour la mesure des forces, du couple, du travail, de la puissance ou du rendement mécanique
G01R 31/27 - Test de dispositifs sans les extraire physiquement du circuit dont ils font partie, p.ex. compensation des effets dus aux éléments environnants
G01R 31/36 - Dispositions pour le test, la mesure ou la surveillance de l’état électrique d’accumulateurs ou de batteries, p.ex. de la capacité ou de l’état de charge
A system and method to release a subject device includes a passage associated with the subject device, the passage having a first end and a second end, at least one hinged door associated with the second end of the passage, and at least one urging member to urge the at least one hinged door closed and to selectively open the at least one hinged door in response to the subject device contacting the at least one hinged door.
A de-linking assembly includes an actuator defining a chamber and an inlet, a piston slideably disposed within the chamber, link coupled to the actuator, and a ram disposed between the piston and the link. The link defines a stress concentration features and a load point on a side of the link on a side of the stress concentration feature opposite the actuator. The ram is seated to the piston and against the load point such that air introduced into the chamber through the inlet applies force to the piston and ram sufficient to sever the link by inducing stress in the stress concentration feature.
F17C 5/06 - Procédés ou appareils pour remplir des récipients sous pression de gaz liquéfiés, solidifiés ou comprimés pour le remplissage avec des gaz comprimés
A propulsor hub is provided and includes a casing including an inner annular part and blade-connection parts extending outwardly from the inner annular part, a liner having inner and outer opposed radial ends, the liner being disposed about a corresponding one of the blade-connection parts with the inner radial end thereof at a distance from the inner annular part and a weighted element securely disposed about the corresponding one of the blade-connection parts to abut the outer radial end of the liner.
B64C 27/82 - Giravions; Rotors propres aux giravions caractérisés par l'existence d'un rotor auxiliaire ou d'un dispositif à jet fluide pour contrebalancer le couple du rotor de sustentation ou faire varier la direction du giravion
A control system is provided and includes a servo control system configured to control aerodynamic element pitching, an optical sensor system disposed along rotor blades to generate an optical response reflective of rotor feedback states of the rotor blades and a processing unit operably coupled between the servo control and optical sensor systems, the processing unit being configured to calculate strain in the rotor blades from the optical response, convert the calculated strain into readings of the rotor feedback states and issue a servo command to the servo control system as an instruction for controlling the aerodynamic element pitching.
B64C 27/39 - Rotors comportant des articulations les pales étant articulées séparément, c. à d. avec des articulations de battement ou de traînée
B64C 27/57 - Mécanismes pour la commande du réglage ou du mouvement de la pale par rapport à la tête du rotor, p.ex. mouvement de traînée caractérisés par les dispositifs de déclenchement de la commande, p.ex. à commande manuelle automatiques ou sensibles à certains facteurs, p.ex. sensibles à la vitesse du rotor, au couple ou à la poussée
A method for prognostic modeling includes obtaining probability values for possible health states of a system or component part using one or more data driven models and one or more physics of failure models. A probabilistic network is built using a plurality of observed and latent variables. The probable outcomes from the one or more physics of failure models and the one or more data driven models are combined to create an integrated model for failure prognosis. A health state of the system or system component is predicted using the integrated model and the probabilistic network.
A system and method for determining a remaining useful life of a component, includes providing a usage and configuration information associated with the component, determining if a preexisting spall condition exists for the component, executing a spall initiation model for the component if the preexisting spall condition does not exist, wherein the spall initiation model provides a spall initiation life associated with the component by analyzing the usage and configuration information, executing a spall propagation model for the component, wherein the spall propagation model provides a spall propagation life associated with the component by analyzing the usage and configuration information, and providing a remaining useful life by integrating the spall initiation life and the spall propagation life.
G01D 3/08 - Dispositions pour la mesure prévues pour les objets particuliers indiqués dans les sous-groupes du présent groupe avec dispositions pour protéger l'appareil, p.ex. contre les fonctionnements anormaux, contre les pannes
A system for strain gage calibration includes a data acquisition system operable to receive sensor inputs from a force sensor as a force input and a strain gage as a strain output. The strain gage detects a strain measurement of a structure under test in response to an excitation force applied by an excitation device, and the force sensor detects the excitation force. The system also includes a data processing system operable to perform calibration feature extraction of a plurality of calibration features from time and frequency domain responses of the force input and the strain output, and to determine a calibration factor of the strain gage based on a correlation of the calibration features to reference calibration features. The force input and the strain output are preprocessed before the calibration feature extraction to filter noise, remove outlying data, and temporally align the force input and the strain output.
A method for position hold override control of an aircraft includes determining, by a processor, that a position hold mode is enabled to hold the aircraft at a substantially fixed position with respect to a target. The processor receives a control input indicative of a commanded change in acceleration of the aircraft as an override of the position hold mode. The processor determines an acceleration command based on the commanded change in acceleration. The acceleration command is adjusted as an adjusted acceleration command responsive to a non-linear scheduled translational rate command based on feedback of a commanded velocity of the aircraft. An update to the commanded velocity of the aircraft is generated based on the adjusted acceleration command.
B64C 13/02 - Dispositifs amorçant la mise en œuvre
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. pilote automatique
G05D 1/08 - Commande de l'attitude, c. à d. élimination ou réduction des effets du roulis, du tangage ou des embardées
G05D 5/00 - Commande en vue d'obtenir des dimensions déterminées d'un matériau
A connector assembly to connect a swashplate and a rotor shaft or hub is provided. The connector assembly includes a mount configured to fixedly connect to the rotor shaft or hub, a sleeve pivotably attached to the mount, and a translating element translationally retained within the sleeve and configured to engage with the swashplate such that the swashplate and the rotor shaft or hub rotate at the same rotational speed.
B64C 27/605 - Transmissions, p.ex. en liaison avec les moyens déclenchant ou agissant sur les pales mécaniques comportant un plateau oscillant, des mécanismes à tringlerie ou à came
B64C 27/59 - Transmissions, p.ex. en liaison avec les moyens déclenchant ou agissant sur les pales mécaniques
A gearbox for a rotary wing aircraft including a sump, a primary lubricant reservoir fluidically connected to the sump, one or more primary lubricant jets fluidically connected to the primary lubricant reservoir, an auxiliary lubricant reservoir fluidically connected to the sump, one or more auxiliary lubricant jets fluidically connected to the auxiliary lubricant reservoir, and at least one valve selectively fluidically connecting the sump and the primary lubricant reservoir based on a first lubricant pressure and the sump and the auxiliary lubricant reservoir based on a second lubricant pressure at the at least one valve.
A system for starting a gas turbine engine includes a rotor drive system and a hydraulic motor system operatively connected to the rotor drive system. A gas turbine engine is operatively connected to the hydraulic motor system for starting the gas turbine engine. A method for starting an engine includes initiating single-engine-operation on a multi-engine aircraft. Single-engine operation includes operating a first engine and powering down a second engine. The method includes running a hydraulic motor system. The hydraulic motor system is driven by the rotor drive system and is operatively connected to the second engine. The method includes identifying a need to start the second engine and starting the second engine using the hydraulic motor system.
F02N 7/08 - Appareils de démarrage comportant un moteur ou un appareil auxiliaire entraîné par fluide les moteurs étant du type rotatif
F02N 7/12 - Appareils de démarrage comportant un moteur ou un appareil auxiliaire entraîné par fluide caractérisés par l'utilisation de moteurs ou appareils auxiliaires du type "à combustion" les moteurs étant du type rotatif, p.ex. des turbines
F02N 7/14 - Appareils de démarrage comportant un moteur ou un appareil auxiliaire entraîné par fluide caractérisés par l'utilisation de moteurs ou appareils auxiliaires du type "à combustion" les moteurs de démarrage pouvant être rapidement retirés des moteurs principaux, p.ex. du type portatif
68.
GUST ALLEVIATING CONTROL FOR A COAXIAL ROTARY WING AIRCRAFT
One aspect is a flight control system for a coaxial rotary wing aircraft including a main rotor system and an active elevator. The flight control system includes a flight control computer with processing circuitry that executes control logic. The control logic includes a gust detector that produces a gust error indicative of a wind gust encountered by the coaxial rotary wing aircraft. The control logic also includes a gust alleviation control that reduces lift on the main rotor system with collective, based on the gust error, and mixes a collective command to a main rotor cyclic and a differential cyclic to reduce an aircraft pitch response and a lift-offset change. The gust alleviation control also reduces a main rotor pitching moment with the main rotor cyclic, based on the gust error, and mixes a main rotor cyclic command to the active elevator to reduce the aircraft pitch response.
B64C 1/16 - Fuselages; Caractéristiques structurales communes aux fuselages, voilures, surfaces stabilisatrices ou organes apparentés spécialement adaptés pour le montage du groupe propulseur
B64C 27/10 - Hélicoptères à plusieurs rotors disposés coaxialement
G05D 1/04 - Commande de l'altitude ou de la profondeur
G05D 1/08 - Commande de l'attitude, c. à d. élimination ou réduction des effets du roulis, du tangage ou des embardées
G05D 1/10 - Commande de la position ou du cap dans les trois dimensions simultanément
69.
INLET GUIDE VANE CONTROL FOR AIRCRAFT SINGLE ENGINE OPERATION
A method of operating a multi-engine, rotary wing aircraft in a single engine, in-flight mode, the method includes stopping a first engine while operating a second engine; closing variable inlet guide vanes on the first engine; and turning a gas generator of the first engine at a reference rotational speed.
B64C 27/18 - Entraînement des rotors par dispositifs, p.ex. des propulseurs, montés sur les pales du rotor le dispositif étant du type à jet réactif
F02C 9/22 - Commande du débit du fluide de travail par réglage des aubes par réglage des aubes de turbine
F02C 9/54 - Commande de l'alimentation en combustible combinée avec une autre commande de l'ensemble fonctionnel avec la commande du flux du fluide de travail par étranglement du passage du fluide de travail, par réglage des aubes
70.
EXTERNAL LOAD MANAGEMENT FUNCTIONS FOR VERTICAL TAKE-OFF AND LANDING AIRCRAFT
According to an aspect, a system in an aircraft includes a vehicle management system (VMS) and a load control system (LCS). The LCS includes an LCS processor operable to receive and transmit a plurality of data and load management commands to one or more of: the VMS and a load control interface. The LCS processor is further operable to interact with one or more of: the VMS, one or more LCS sensors, and a load capturing interface of the aircraft to execute the load management commands as a sequence of one or more load management subcommands. The load capturing interface is operable to capture and release an external load relative to the aircraft using a load capture device. The LCS processor is also operable to report a status of execution of the load management commands to the VMS and the load control interface.
G01C 23/00 - Instruments combinés indiquant plus d’une valeur de navigation, p.ex. pour l’aviation; Dispositifs de mesure combinés pour mesurer plusieurs variables du mouvement, p.ex. la distance, la vitesse ou l’accélération
G06F 17/00 - TRAITEMENT ÉLECTRIQUE DE DONNÉES NUMÉRIQUES Équipement ou méthodes de traitement de données ou de calcul numérique, spécialement adaptés à des fonctions spécifiques
G06F 19/00 - Équipement ou méthodes de traitement de données ou de calcul numérique, spécialement adaptés à des applications spécifiques (spécialement adaptés à des fonctions spécifiques G06F 17/00;systèmes ou méthodes de traitement de données spécialement adaptés à des fins administratives, commerciales, financières, de gestion, de surveillance ou de prévision G06Q;informatique médicale G16H)
A measuring system, method, and/or computer program that realizes physics-based relations between sensor readings to monitor for degradations and predict failures of power systems is provided. For example, the supply and return of fuel in a power system is provided by a fuel injection system. The fuel injection system responds to changes in loads and system conditions, such as to compensate for fuel loss due to fuel combustion, by continuously and instantaneously changing the fuel flow. This behavior by the fuel injection system creates characteristic signatures. These characteristic signatures are instantaneously detected and utilized by the measuring system, method, and/or computer program to detect healthy, degrading, failing, and failed mechanical conditions so as to monitor for degradations and predict failures of the power system.
A method of monitoring health of a hydraulic pump includes identifying, from performance data received from a sensor coupled to a hydraulic system, intervals of steady state and transient state operation. Dynamic element indicators are determined using data from the interval of steady state operation. Performance indicators are determined using data from both the interval of steady state operation and the interval of transient state operation. One or more state flags are set using the dynamic element indicators and the performance indicators.
F04B 51/00 - Tests des "machines", pompes ou installations de pompage
B64C 13/00 - Systèmes de commande ou systèmes de transmission pour actionner les gouvernes, les volets hypersustentateurs, les aérofreins ou les destructeurs de portance (spoilers)
A system and method for controlling an altitude loss of an aircraft in response to a power loss event, includes obtaining at least one aircraft condition from at least one sensor, determining a present aircraft energy state of the aircraft from the at least one aircraft condition via an energy analysis unit, wherein the present aircraft energy state includes an aircraft potential energy and at least one of an aircraft kinetic energy and a rotor rotational kinetic energy, calculating a flight path to partially utilize at least one of the aircraft kinetic energy and the rotor rotational kinetic energy to initiate an autorotation state of the aircraft via a flight path controller, wherein the flight path controller minimizes an aircraft potential energy loss associated with the flight path, and initiating the autorotation state of the aircraft via the flight path.
A method of carburizing a steel component having a composition of Fe-16.3Co-7.5Ni-3.5Cr-1.75Mo-0.2W-0.11C-0.03Ti-0.02V includes generating a low pressure vacuum in a carburization furnace having the steel component therein, heating the steel component to an optimal carburization temperature while in the low pressure vacuum, performing a boost cycle to introduce carbon rich gas into the carburization furnace while the steel component is at the optimal carburization temperature and in the low pressure vacuum, and performing a diffuse cycle by ceasing introduction of the carbon rich gas into the carburization furnace to allow for diffusion of the carbon into the steel component to occur and while the steel component is at the optimal carburization temperature and in the low pressure vacuum. The boost cycle and the diffuse cycle are repeated to achieve a carbon content at a surface of the steel component of between 0.40 wt. % and 0.55 wt. %.
C23C 8/00 - Diffusion à l'état solide uniquement d'éléments non métalliques dans la couche superficielle de matériaux métalliques; Traitement chimique de surface par réaction entre le matériau métallique de la surface et un gaz réactif, laissant dans le revêtement des produits de la réaction, p.ex. revêtement de conversion, passivation des métaux
A method of manufacturing a fabricated part having complex geometry is provided. The method includes generating a digital model of a tooling having a complex geometry; additively manufacturing a tooling based on the digital model from tooling material; laying-up fabrication materials on the tooling; curing the fabrication materials on the tooling to form a fabricated part; and removing the tooling from the fabricated part.
B29C 39/40 - Dispositions pour compenser des changements de volume, p.ex. le retrait
B29C 63/22 - Garnissage ou gainage, c. à d. application de couches ou de gainages préformés en matière plastique; Appareils à cet effet avec des couches ou des gainages ayant une forme adaptée à celle de l'objet
B29C 33/38 - Moules ou noyaux; Leurs détails ou accessoires caractérisés par la matière ou le procédé de fabrication
G06F 19/00 - Équipement ou méthodes de traitement de données ou de calcul numérique, spécialement adaptés à des applications spécifiques (spécialement adaptés à des fonctions spécifiques G06F 17/00;systèmes ou méthodes de traitement de données spécialement adaptés à des fins administratives, commerciales, financières, de gestion, de surveillance ou de prévision G06Q;informatique médicale G16H)
A fuel supply system for an aircraft includes a fuel tank configured to supply fuel to an engine of an aircraft, a boost pump in operational communication with the fuel tank, wherein the boost pump is configured to control at least one of a fuel level and a fuel pressure in the fuel tank, and an electronic controller in communication with the boost pump and configured to control the boost pump. The electronic controller is configured to receive received information including (i) fuel information, (ii) flight information, and (iii) aircraft information, and configured to control the boost pump based on the received information.
A method for monitoring a health state of electronic equipment is provided and includes capturing data of an operation of the electronic equipment over a sampling range of predefined length, storing captured data in a storage unit and characterizing a behavior of the operation of the electronic equipment based on an analysis of stored captured data in an event a predefined time has expired or the storage unit has reached maximum capacity.
G01R 31/00 - Dispositions pour tester les propriétés électriques; Dispositions pour la localisation des pannes électriques; Dispositions pour tests électriques caractérisées par ce qui est testé, non prévues ailleurs
A bonding preparation patch for application to a resin treated surface is provided. The patch includes a strip having first and second portions, each of which has corresponding first and second sides. The strip is formed of resin porous material and is foldable such that the respective first sides of the first and second portions face each other. The patch further includes a resin barrier interposable between corresponding portions of the respective first sides and a tape including at least one adhesive side, which is securable relative to the first portion and disposable in contact with the second side of the second portion.
B32B 3/04 - Caractérisés par des caractéristiques de forme en des endroits déterminés, p.ex. au voisinage des bords caractérisés par une couche pliée au bord, p.ex. par-dessus une autre couche
B32B 3/26 - Produits stratifiés caractérisés essentiellement par le fait qu'une des couches comporte des discontinuités ou des rugosités externes ou internes, ou bien qu'une des couches est de forme générale non plane; Produits stratifiés caractérisés essentiellement par des particularismes de forme caractérisés par une couche comportant des cavités ou des vides internes
B32B 7/06 - Liaison entre couches permettant une séparation sans difficultés
B32B 7/10 - Liaison entre couches au moins une des couches ayant des propriétés inter-réactives
B32B 7/14 - Liaison entre couches utilisant des adhésifs interposés ou des matériaux interposés ayant des propriétés adhésives appliqués en disposition espacée, p.ex. en bandes
B32B 38/10 - Enlèvement de couches ou de parties de couches, mécaniquement ou chimiquement
According to an aspect of the invention, a method of flight initiation proximity warning for an autonomous vehicle is provided. A flight initiation request is detected at a processing system of the autonomous vehicle. A preflight proximity scan is performed for any obstacles within a predetermined distance from the autonomous vehicle based on the flight initiation request. An alert is sent to a control station based on detecting at least one obstacle within the predetermined distance. Flight initiation of the autonomous vehicle is inhibited until an acknowledgement of the alert is received at the processing system of the autonomous vehicle.
G01S 13/00 - Systèmes utilisant la réflexion ou la reradiation d'ondes radio, p.ex. systèmes radar; Systèmes analogues utilisant la réflexion ou la reradiation d'ondes dont la nature ou la longueur d'onde sont sans importance ou non spécifiées
80.
SYSTEMS AND METHODS FOR REMOTELY TRIGGERED DATA ACQUISITION
A method of data acquisition for health management of systems is provided. The method includes receiving, at a remote node, analog data from one or more sensors configured to monitor a health characteristic of a system, converting, at the remote node, the analog data into digital data, time stamping the digital data with the remote node, recording the digital data in a memory of the remote node, wherein the memory is a ring buffer, transmitting, from the remote node to a central device, requested digital data upon receiving a request related to a triggering event, and synchronizing the transmitted data at the central device based on the time stamp of the requested digital data to generate synchronized data.
A method of trajectory control for a vehicle includes obtaining an initial trajectory; presenting the initial trajectory as a current trajectory on an I/O device, the current trajectory presented overlaying terrain; initiating travel of the vehicle along the current trajectory; updating the current trajectory and the terrain in real time as the vehicle travels along the current trajectory; determining if change in the current trajectory is required; changing the current trajectory to an altered trajectory in response to determining change in the current trajectory is required; and presenting the altered trajectory on the I/O device, the altered trajectory presented overlaying the terrain.
A system and method for preventing a flame out condition in at least one engine, includes detecting a moisture content exceeding a threshold moisture content in an operating environment of the at least one engine, and engaging at least one igniter associated with the at least one engine in response to the moisture content.
F02D 45/00 - Commande électrique non prévue dans les groupes
F02P 5/04 - Avance ou retard à l'allumage par étincelle électrique; Leur commande automatiquement, en fonction des conditions de travail du moteur, du véhicule ou des conditions atmosphériques
A heater mat assembly for a blade using an electrical current is provided including a first heating element region configured to generate a first amount of heat using the electrical current and disposed at a first region of the heater mat assembly. A second heating element region extends form the first heating element region and is configured to generate a second amount of heat using the electrical current. The second amount of heat is different than the first amount of heat.
B64D 15/14 - Dégivrage ou antigivre des surfaces externes des aéronefs par chauffage électrique commandé cycliquement sur la longueur de la surface
B64D 15/22 - Mise en action automatique par détecteur de givrage
H05B 3/34 - Eléments chauffants ayant une surface s'étendant essentiellement dans deux dimensions, p.ex. plaques chauffantes flexibles, p.ex. grillages ou tissus chauffants
A tool system is provided and includes a securing element, a hammer element configured to drive a member toward the securing element and first and second orientation elements rigidly disposed on the securing and hammer elements, respectively. The securing and hammer elements have respective operational axes and the first and second orientation elements respectively include orientation sensors configured to cooperatively determine a relative orientation of the respective operational axes.
A system for providing fleet analytic services for a fleet includes a fleet interface to receive fleet data associated with operation and maintenance of the fleet; a memory to store the fleet data; a processor to implement a plurality of fleet analytic services modules to process and analyze fleet data for opportunities to improve maintenance, operations, costs, readiness, health and supply/logistics; a user input/output interface to receive commands from a user and output results of the plurality of fleet analytic services modules.
A fluid condition monitoring device includes a sensing assembly including a sensor and a transducer, the sensor to sense a property of the fluid and the transducer to apply a test signal to the fluid and receive a return signal from the fluid; a control assembly coupled to the sensing assembly, the control assembly including a controller and an input/output interface, the controller interfacing with the transducer to generate fluid condition information in response to the return signal; and an interface assembly coupled to the control assembly, the interface assembly including a connection to the input/output interface to transmit the fluid condition information to an external system.
A gas turbine exhaust assembly includes an exhaust flow path configured to receive an exhaust flow from a gas turbine engine, the exhaust flow path defined by an inner hub and a radially outer wall. The gas turbine exhaust assembly also includes a plurality of vanes circumferentially spaced from each other and operatively coupled to the radially outer wall of the exhaust flow path, each of the plurality of vanes extending only partially toward the inner hub and terminating at an inner end of the vanes, the inner end defining an open portion.
A method of tip clearance estimation for a rotor blade is provided. The method includes measuring blade deflection of the rotor blade, generating a harmonic function for the rotor blade from the measured blade deflection, predicting tip displacement of the rotor blade using the generated harmonic function and adjusting a position of the rotor blade according to the predicted tip displacement.
A system for sensing data in an aircraft, includes a plurality of wireless sensors, a receiver to sample a random subset of the plurality of wireless sensors at each of a plurality of times to generate a data matrix with a plurality of sampled entries and a plurality of missing entries, and an analysis unit to analyze the data matrix to provide a plurality of solutions corresponding to the plurality of missing entries using numerical analysis.
A pin of a hinge system movable between a first position and a second position is provided, wherein in the first position, the pin is received within a first component and a second component. The pin includes a cylindrical body coupled to an actuator for movement along an axis between the first position and the second position. A tip is removably attached to an end of the cylindrical body. The tip is configured to contact at least one of the first component and the second component when the pin is in the first position.
E05D 3/02 - Charnières ou gonds à broches à une broche
E05D 3/04 - Charnières ou gonds à broches à une broche mettant en prise au moins trois éléments, p.ex. manchons, mobiles l'un par rapport à l'autre reliant plusieurs battants à un autre élément
E05D 5/10 - Broches, douilles ou manchons; Broches amovibles
E05D 5/12 - Blocages des broches dans les douilles de manière amovible ou non
E05D 7/00 - Charnières, gonds ou pivots de structure particulière
E05D 7/10 - Charnières, gonds ou pivots de structure particulière permettant une séparation facile des éléments à l'axe de la charnière
A method of repairing a composite structure or forming a component of a part is provided. The method includes releasably laying up of a first member that is curable at a first temperature at or above a constrained temperature limit of the composite structure or part, releasably laying up of a second member on the first member that is curable at a second temperature below the constrained temperature limit, curing the second member into a scaffold at the second temperature at the composite structure or part, transferring the first member and the scaffold remotely from the composite structure or part for first member curing and removing the cured first member from the scaffold for bonding of the cured first member to the composite structure or part.
B32B 3/12 - Produits stratifiés caractérisés essentiellement par le fait qu'une des couches comporte des discontinuités ou des rugosités externes ou internes, ou bien qu'une des couches est de forme générale non plane; Produits stratifiés caractérisés essentiellement par des particularismes de 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
92.
ESTIMATING DYNAMIC THRUST OR SHAFT POWER OF AN ENGINE
A measuring system is provided that includes a turbine engine thrust estimator that computes "virtual measurements" of dynamic engine thrust and other parameters of interest from test cell data in a very short amount of time. The measuring system 'tunes' a user's engine model, in a numerical propulsion system simulation, by optimizing system biases and health parameters to match the sensor outputs of a set of steady state data points across the operating range. The tuned model is then utilized by the measuring system to create a constant gain extended Kalman filter that is added directly within a code of the numerical propulsion system simulation. Results, including thrust, from the numerical propulsion system simulation with Kalman filter are then presented as 'actual' corrected data.
G01L 5/13 - Appareils ou procédés pour la mesure des forces, du travail, de la puissance mécanique ou du couple, spécialement adaptés à des fins spécifiques pour la mesure de la puissance de traction ou propulsive des véhicules
93.
FLUID DISTRIBUTION ASSEMBLY HAVING ANTI-CLOG INLET HOUSING
A fluid distribution assembly for distributing a fluid, the fluid distribution assembly includes an inlet housing including a first conduit and a bypass conduit; a chip detector cavity in fluid communication with the first conduit such that the fluid can pass through the first conduit into the chip detector cavity; and an outlet housing in fluid communication with the chip detector cavity and the bypass conduit such that the fluid can pass into the outlet housing through the chip detector cavity and/or the bypass conduit.
A bond is provided and includes a substrate having a first surface, a bond structure having a second surface and a bonding assembly adhesively disposed between complementary portions of the first and second surfaces. The bonding assembly includes discrete bond elements configured to form first and second adhesive zones with local sections of the complementary portions of the first and second surfaces. The discrete bond elements are displaced such that the respective first and second adhesive zones are correspondingly displaced and define discontinuous bond lines.
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
95.
SELF-POWERED MULTI-FUNCTIONAL STRUCTURAL HEALTH MONITORING SENSOR
A structural health monitoring module including a sensor attached to a surface of a structural member configured to convert a strain on the structural member to electric energy, a gate operationally connected to the sensor and configured to control distribution of the energy, an energy storage device operationally connected to the gate and configured to receive the energy from the sensor, a data collection device configured to receive the energy from the sensor and at least one of process and record data related to the received energy, and a data transmission device configured to wirelessly transmit data from the data collection device to an external receiver. The gate is configured to direct a portion of the energy to the storage device in a storage state and configured to direct a portion of the energy to the data collection device when in load monitoring or interrogation states.
A method of manufacturing a part is provided. The method includes heating a gear in the presence of carbon to carburize a material of the gear to create a carburized gear, the gear having a plurality of gear teeth and which comprises a selected material. Next, the carburized gear is high pressure gas quenched to drive the carbon into the material of the gear to create a quenched gear. Next, the quenched gear is at least one of cavitation peened and laser peened to create a peened gear. Finally, superfinishing is performed on surfaces of the peened gear.
An aircraft is provided and includes a fuselage including a top and a tail, a main rotor apparatus disposed at the top of the fuselage, which rotates one or more rotors to generate lift, and an active flow control (AFC) system. The AFC system includes plasma actuators configured to generate plasma at a location adjacent to the main rotor apparatus and/or at the tail of the fuselage.
A rotary winged aircraft includes an airframe and a drive system located at the airframe. A main rotor system is positioned at the airframe and is operably connected to the drive system to provide lift for the rotary winged aircraft. An auxiliary propulsor is located at the airframe and includes a plurality of propeller blades rotatable about a propulsor axis. Collective and cyclic pitch input applied to the auxiliary propeller blades increases yaw performance of the aircraft. A method of operating a rotary wing aircraft includes powering an auxiliary propulsor secured to an airframe of the aircraft and including a plurality of propeller blades rotatable about a propulsor axis. Individual propeller blades are cyclically rotated about their respective propeller blade axes to cyclically change a propeller blade pitch. Rotation of the aircraft about a yaw axis is induced via the collective and cyclic pitch change of the propeller blades.
B64C 27/00 - Giravions; Rotors propres aux giravions
B64C 27/82 - Giravions; Rotors propres aux giravions caractérisés par l'existence d'un rotor auxiliaire ou d'un dispositif à jet fluide pour contrebalancer le couple du rotor de sustentation ou faire varier la direction du giravion
An elastomeric bearing configured for use in a rotor blade assembly is provided including an inner race, and an outer race. An outer damper portion is arranged adjacent the outer race and an inner snubber portion is arranged adjacent the inner race. A rigid transition layer is disposed between the outer damper portion and the inner snubber portion. The rigid transition layer has a generally circular cross-section except at a segment which has been removed and which defines a generally planar surface at a chord of the segment. The generally planar surface is configured to contact a surface of an adjacent component.
According to an aspect of the invention, a method of trajectory-based sensor planning for a vehicle includes receiving an indication of a planned change in a trajectory of the vehicle. A processing subsystem determines a current field of view of a directional sensor and a planned adjustment in the current field of view of the directional sensor relative to the vehicle to align with the planned change in the trajectory of the vehicle. The planned adjustment in the current field of view of the directional sensor is initiated prior to changing the trajectory of the vehicle.
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