One embodiment is a system including a component for installation on a vehicle comprising a central maintenance computer (“CMC”); a configuration/maintenance module (“CMM”) associated with the component and including memory for storing component information, a sensor for detecting a condition and generating data indicative thereof; a microprocessor for processing the sensor data and updating the component information with the processing results; and a communications interface between the CMM and the CMC. The system further includes a remaining useful life (“RUL”) module associated with the component that periodically updates an RUL, the RUL module periodically updating an RUL value for the component and communicating the updated RUL value to the CMM for storage in the memory. The CMC communicates with the CMM to update the component information included in the memory based on information input to the CMC by a user or changes in a condition of the vehicle.
G07C 5/00 - Enregistrement ou indication du fonctionnement de véhicules
B64F 5/60 - Test ou inspection des composants ou des systèmes d'aéronefs
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 bonded part includes a first surface facing toward a second surface, and a cured adhesive between the first and second surfaces defining a bond line. A surface structure on the first surface is within the bond line and has surface protrusions arranged in a pattern. Each surface protrusion protrudes outwardly from a first end at the first surface to a second end adjacent to the second surface. A thickness of the surface protrusions is substantially equal to the thickness of the bond line. The cured adhesive extends around the surface protrusions. The thickness of the bond line between the first and second surfaces is substantially constant along the bond line, and is greater than a thickness of the cured adhesive between the second ends of the protrusions and the second surface.
B32B 3/30 - 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 continue dont le périmètre de la section droite a une allure particulièreProduits 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 comportant des cavités ou des vides internes caractérisés par une couche comportant des retraits ou des saillies, p. ex. des gorges, des nervures
B32B 7/12 - Liaison entre couches utilisant des adhésifs interposés ou des matériaux interposés ayant des propriétés adhésives
B32B 5/02 - Produits stratifiés caractérisés par l'hétérogénéité ou la structure physique d'une des couches caractérisés par les caractéristiques de structure d'une couche comprenant des fibres ou des filaments
B32B 15/14 - Produits stratifiés composés essentiellement de métal adjacent à une couche fibreuse ou filamenteuse
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
In an embodiment, a method includes monitoring environmental conditions via a plurality of sensors positioned in proximity to a vehicle. The method also includes receiving, from one or more of the plurality of sensors, a first measured value of a first environmental variable and at least one additional measured value of at least one additional environmental variable. In addition, the method includes automatically determining, via a machine-learning model, a first expected value of the first environmental variable given the at least one additional measured value of the at least one additional environmental variable. Furthermore, the method includes automatically generating a storage decision in relation to the first measured value based, at least in part, on an evaluation of the first measured value relative to the first expected value. Additionally, the method includes causing execution of the storage decision at least with respect to onboard storage of the vehicle.
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
H03M 7/30 - CompressionExpansionÉlimination de données inutiles, p. ex. réduction de redondance
H04L 29/08 - Procédure de commande de la transmission, p.ex. procédure de commande du niveau de la liaison
H04W 4/48 - 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 dans le véhicule
An exemplary liquid tank level measurement system includes a tank having a wall, an accelerometer attached to the wall and configured to measure a vibration in the wall, and an instrument electronically connected to the accelerometer, the instrument configured to communicate a liquid level condition responsive to a vibration measurement received from the accelerometer.
An inboard beam includes a body having an upper flange and a lower flange coupled thereto. The upper flange includes a first upper inboard aperture and an upper outboard aperture formed therein. The lower flange includes a first lower inboard aperture and a lower outboard aperture formed therein. An upper beam fitting is coupled to the upper flange and lower beam fitting is coupled to the lower flange. The upper beam fitting includes a first upper inboard post. The upper beam fitting includes an upper outboard post extending parallel to the inboard post. The lower beam fitting includes a first lower inboard post. The lower beam fitting includes a lower outboard post extending parallel to the lower inboard post.
A method of increasing a stability speed of a tiltrotor aircraft includes pivoting a rotor assembly having at least three rotor blades from a first position for operating the tiltrotor aircraft in a helicopter mode to a second position for operating the tiltrotor aircraft in an airplane mode, and increasing a stiffness of the rotor assembly when the rotor assembly is in the second position.
An exemplary rotorcraft includes a power train with an engine coupled to a gearbox, a main rotor blade having a mast coupled to the power train, a control input linkage in communication between a pilot input device and the main rotor blade configured to communicate a control input force from the pilot input device to the main rotor blade, and a counterweight system in connection with the control input linkage and the power train to apply a centrifugal force to the control input linkage.
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
A parasite aircraft for airborne deployment and retrieve includes a wing; a fuselage rotatably mounted to the wing; a dock disposed on top of the fuselage and configured to receive a maneuverable capture device of a carrier aircraft; a pair of tail members extending from the fuselage; and a plurality of landing gear mounted to the wing. A method of preparing a parasite aircraft for flight includes unfolding an end portion of a wing; unfolding an end portion of a tail member of the parasite aircraft; and rotating a fuselage of the parasite aircraft so that the fuselage is perpendicular to the wing. A method of preparing a parasite aircraft for storage includes rotating a fuselage of the parasite aircraft to be parallel with a wing of the parasite aircraft; folding an end portion of the wing; and folding an end portion of a tail member of the parasite aircraft.
In one embodiment, a method is performed by a computer system in an aircraft. The method includes receiving an advance indication of a take-off or landing event to be executed by the aircraft in proximity to a landing area such that the landing area includes an arrangement of a plurality of emitters of electromagnetic radiation. The method further includes, responsive to the receiving, detecting, via a sensor in communication with the computer system, emission states of at least some of the plurality of emitters. In addition, the method includes transforming the detected emission states into an instruction set for the take-off or landing event. The method also includes initiating monitoring of the aircraft relative to the instruction set as the aircraft executes the take-off or landing event in proximity to the landing area.
An aircraft includes a variable-speed gearbox. The variable-speed gearbox includes a low-speed gear train and a high-speed gear train, each gear train of which is configured to selectively provide torque from an engine of the aircraft to a proprotor. The variable-speed gearbox also includes a hydraulic system configured to provide torque to the proprotor. The hydraulic system includes a hydraulic pump driven by the engine of the tiltrotor aircraft and a variable-displacement motor driven by a hydraulic fluid from the hydraulic pump.
F16H 61/02 - Fonctions internes aux unités de commande pour changements de vitesse ou pour mécanismes d'inversion des transmissions transmettant un mouvement rotatif caractérisées par les signaux utilisés
F16H 61/12 - Détection d'un dysfonctionnement ou d'un dysfonctionnement potentiel, p. ex. dispositif de sécurité positive
F16H 3/083 - Transmissions à engrenages pour transmettre un mouvement rotatif à rapport de vitesse variable ou pour inverser le mouvement rotatif sans engrenages à mouvement orbital exclusivement ou principalement à engrenages constamment en prise, pouvant être libérés de leurs arbres avec des éléments d'embrayage à action radiale et à commande axiale, p. ex. des clavettes coulissantes
F16H 3/097 - Transmissions à engrenages pour transmettre un mouvement rotatif à rapport de vitesse variable ou pour inverser le mouvement rotatif sans engrenages à mouvement orbital exclusivement ou principalement à engrenages constamment en prise, pouvant être libérés de leurs arbres caractérisés par l'agencement des engrenages avec plusieurs arbres de renvoi les arbres d'entrée et de sortie étant alignés sur le même axe
F16H 61/00 - Fonctions internes aux unités de commande pour changements de vitesse ou pour mécanismes d'inversion des transmissions transmettant un mouvement rotatif
B64C 29/00 - Aéronefs capables d'atterrir ou de décoller à la verticale, p. ex. aéronefs à décollage et atterrissage verticaux [ADAV, en anglais VTOL]
B64D 35/04 - Transmission de la puissance des groupes moteurs aux hélices ou aux rotorsAménagements des transmissions caractérisée par le fait que la transmission entraîne plusieurs hélices ou rotors
F16H 47/02 - Combinaisons d'une transmission mécanique avec des embrayages à fluide ou une transmission à fluide la transmission à fluide étant du type volumétrique
An aircraft having an electric motor coupled to a rotor and an instrument electronically connected to the electric motor and configured to communicate a time available value before a motor condition reaches a motor condition limit.
B64D 31/06 - Dispositifs amorçant la mise en œuvre actionnés automatiquement
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’aviationDispositifs de mesure combinés pour mesurer plusieurs variables du mouvement, p. ex. la distance, la vitesse ou l’accélération
A method of blade fold for a tiltrotor aircraft includes configuring the tiltrotor aircraft in a flight ready position with a rotor system in an inverted-Y position, unlocking a first rotor blade of the rotor system to permit the first rotor blade to pivot relative to a yoke of the rotor system, restraining the first rotor blade to allow the first rotor blade to pivot relative to the yoke as the yoke is rotated, rotating the rotor system in a first direction so that the first rotor blade pivots closer to a second rotor blade, rotating the rotor system in a second direction to orient the rotor system into a modified inverted-Y position, unlocking a third rotor blade to allow the third rotor blade to pivot relative to the yoke as the yoke is rotated, and rotating the rotor system in the second direction so that the third rotor blade pivots closer to the second rotor blade.
The aircraft includes a rotor. The rotor includes a plurality of rotor blades. The aircraft further includes a non-rotating aircraft component. A proximity sensor is disposed with at least one of the non-rotating aircraft component and the rotor blades. A flight control computer is electrically coupled to the proximity sensor.
B64C 27/00 - GiravionsRotors propres aux giravions
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
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]
14.
Blade fold method and apparatus for a tilt rotor hub
A folding rotor blade assembly includes a blade fold support and a blade-fold actuator system coupled to the blade fold support. The blade-fold actuator system includes a motor, a tab configured to selectively prevent rotation of a blade tang of a rotor blade, and a cam connected to the blade fold support and coupled to the motor, the cam configured to move the tab between a locked position that prevents rotation of the blade tang and an unlocked position that permits rotation of the blade tang.
B64C 27/50 - Pales repliables pour faciliter le rangement de l'aéronef
F16H 37/12 - Transmissions comportant principalement une transmission à engrenages ou à friction, des maillons ou des leviers, des cames, ou bien des organes appartenant à deux des trois types ci-dessus au moins
B64C 29/00 - Aéronefs capables d'atterrir ou de décoller à la verticale, p. ex. aéronefs à décollage et atterrissage verticaux [ADAV, en anglais VTOL]
B64C 3/56 - Repliage ou rabattement pour réduire l'encombrement de l'aéronef
A blade-fold bushing system includes a splined bushing comprising a first plurality of teeth, a castellated bushing comprising a second plurality of teeth and a shaft portion configured to coaxially fit within the splined bushing, and a lock bushing coaxially aligned with the castellated bushing. A support tool for use with a blade-fold bushing system includes an outer head comprising a third plurality of teeth configured to mesh with the first plurality of teeth of the splined bushing, and an inner head comprising a fourth plurality of teeth configured to mesh with the second plurality of teeth of the castellated bushing.
In one embodiment, a method is performed by a control computer. The method includes receiving a time series of control inputs in relation to a control axis of an aircraft, where the control computer causes actuation in response to each control input in the time series as the control input is received. The method also includes determining aircraft oscillation over a sample period corresponding to the time series. The method also includes evaluating information related to the determined aircraft oscillation using engagement settings associated with a control filter. The method also includes engaging the control filter responsive to the information satisfying the engagement settings, where the engaged control filter systematically attenuates future control inputs in relation to the control axis prior to actuation responsive thereto.
An ice-management method for an aircraft includes scavenging torque from a mast of the aircraft with a system that is configured to provide an ice-management capability. The method includes using the scavenged torque to impart a vibratory force to an arm of the system and imparting the vibratory force from the arm to an inner surface of a spinner of the aircraft via a contact of the arm.
B64D 15/12 - Dégivrage ou antigivre des surfaces externes des aéronefs par chauffage électrique
B64D 15/16 - Dégivrage ou antigivre des surfaces externes des aéronefs par dispositifs mécaniques, p. ex. des gaines ou des bourrelets fixés ou incorporés à la surface et soumis à des pulsations
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 aircraft, including a fixed nacelle disposed on a wing of the aircraft, the fixed nacelle including a nacelle opening; a proprotor pylon disposed on the wing and rotatable relative to the fixed nacelle between a substantially horizontal position and a non-horizontal position, wherein rotation of the proprotor pylon to a non-horizontal position exposes the nacelle opening; and a movable cover disposed on at least one of the wing and fixed nacelle, said movable cover including a plurality of cover members that are movable between a closed position where at least a portion of the cover members collectively form a protective cover in front of the nacelle opening when the proprotor pylon is positioned in the non-horizontal position and a stowed position where at least a portion of the plurality of cover members are stowed. In other aspects, there is provide a method of covering a nacelle opening.
B64C 29/00 - Aéronefs capables d'atterrir ou de décoller à la verticale, p. ex. aéronefs à décollage et atterrissage verticaux [ADAV, en anglais VTOL]
B64D 7/00 - Agencement à bord aéronefs des équipements militaires, p. ex. des armes, des accessoires d'armement ou des blindages de protectionAdaptations des installations d'armement aux aéronefs
F41A 27/20 - Dispositifs d'entraînement pour le pointage des tourelles
B64D 7/04 - Agencement à bord aéronefs des équipements militaires, p. ex. des armes, des accessoires d'armement ou des blindages de protectionAdaptations des installations d'armement aux aéronefs les armes étant des armes à feu fixes
A folding rotor blade assembly for an aircraft a yoke, an inboard beam coupled to the yoke, an inboard centrifugal force bearing coupled to the inboard beam, a grip coupled to the inboard beam, an outboard bearing housing coupled to the grip, and a rotor blade pivotally coupled to the grip by a blade fold bolt that is positioned outboard of the outboard bearing housing.
An exemplary passive oil system includes a reservoir housing configured in operation to rotate around a rotational axis, the reservoir housing defining a reservoir between a top wall, a bottom wall, innermost side, and an outer sidewall; and an outlet positioned adjacent the outer sidewall to discharge a lubrication fluid contained in the reservoir in response to the reservoir housing rotating around the rotational axis.
A masking tool system includes a first masking body and a second masking body. The first masking body includes a bore passing through a portion of the first masking body and a first sealing element disposed on a first end of the first masking body. The second masking body includes a bore passing through the second masking body and a second sealing element disposed on a first end of the second masking body. The system may also include a rod configured to pass through the bores of the first and second masking bodies and to secure the first and second masking bodies to a metallic article placed therebetween. A diagonal length of the masking tool system induces a wobbling rotation during processing.
B24B 35/00 - Machines ou dispositifs pour le superfinissage des surfaces, c.-à-d. pour le travail au moyen de blocs abrasifs animés d'un mouvement de va-et-vient à haute fréquence
An afterbody for a rotor blade of a rotorcraft is unitarily formed of a single material of construction. The afterbody includes an upper surface disposed from a lower surface, a concave leading edge connected to the upper surface and the lower surface, and a trailing edge formed at an intersection of the upper surface with the lower surface.
A standpipe assembly for a rotorcraft includes a slip ring positioned within the mast of the rotorcraft. The slip ring includes a stator rotationally connected to a rotor. A flexible coupling is connected to the stator and a standpipe tube is connected to the flexible coupling. The flexible coupling is capable of angular, axial, and torsional displacement.
H01R 39/34 - Connexions de conducteur pour bagues collectrices
F16D 3/72 - Accouplements extensibles, c.-à-d. avec moyens permettant le mouvement entre parties accouplées durant leur entraînement avec pièces d'accouplement reliées par un ou plusieurs organes intermédiaires avec des fixations aux pièces d'accouplement axialement espacées
F16D 3/52 - Accouplements extensibles, c.-à-d. avec moyens permettant le mouvement entre parties accouplées durant leur entraînement avec pièces d'accouplement reliées par un ou plusieurs organes intermédiaires comportant une bande, un ressort ou un élément analogue continu, engageant les pièces d'accouplement en un certain nombre d'endroits
An example of an aerial vehicle includes a rudder removably connected to the aerial vehicle by a twist lock mechanism. The twist lock mechanism is biased in a locked position by an elastic member.
B64C 39/02 - Aéronefs non prévus ailleurs caractérisés par un emploi spécial
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 hybrid yoke including a center and yoke arms connected to flexure arms. An inboard centrifugal force bearing assembly connects to the yoke arm and a grip and an outboard shear bearing assembly connects to the flexure arm and the grip. In use, the center and yoke arms carry the centrifugal force at a position inboard of the flexure arm.
A tri-hybrid yoke including a center ring connected to a CF fitting connected to flexure arms. An inboard centrifugal force bearing assembly connects to the CF fitting and a grip. An outboard shear bearing assembly connects to the flexure arm and the grip. In use, the center ring and the CF fittings carry the centrifugal force at a position inboard of the flexure arm.
A multi-piece inboard beam assembly for use in a rotor blade assembly of a rotorcraft. The inboard beam assembly includes an inboard beam connected to an inboard beam fitting with an anti-rotational connection. The inboard beam is connected to a yoke via bearings and the inboard beam fitting is connected to a grip in a double shear condition. In use, the grip, the inboard beam fitting with the double shear connection, the inboard beam, a centrifugal force bearing held by the inboard beam, and the yoke carry the centrifugal force created upon rotation of the rotor blade assembly.
A system and method for preventing a maximum asymmetric condition between pylon tilt angles due to a degraded pylon in a fly-by-wire tiltrotor aircraft during transitions between airplane mode and helicopter mode includes a conversion system for imparting movement on a right and left pylon. A flight control computer is operatively connected to a set of transducers for measuring pylon angles. The flight control computer is further connected to a set of actuators which are attached to each pylon. The flight control computer receives flight dynamics input from the set of transducers and/or the pilot and sends pylon command to the set of actuators. The conversion system measures the difference between the pylon angles during the transition and provides a pylon command adjustment if the difference exceeds a preset threshold.
A folding rotor blade assembly for a tiltrotor aircraft comprising a rotor blade pivotally connected to a yoke with dual concentric blade bolts having a common central axis providing a pivotal axis inboard of an outboard shear bearing. In use, the compact folded arrangement of the rotor blades reduces folded aircraft dimensions in response to ever increasing restricted storage space parameters.
A rotor blade assembly for a tiltrotor aircraft comprising a rotor blade pivotally connected to a yoke with dual concentric blade bolts having a common central axis providing a pivotal axis inboard of an outboard CF bearing and the yoke tip. In use, the compact folded arrangement of the rotor blades reduces folded aircraft dimensions in response to ever increasing restricted storage space parameters.
A folding yoke comprising a bilateral center yoke pivotally connected to separate foldable yoke arms permits rotor blade fold about a single through bolt connection inboard of a set of bearings. In use, the compact folded arrangement of the rotor blades reduces folded aircraft dimensions in response to ever increasing restricted storage space parameters.
F04F 5/16 - Pompes à jet, p. ex. dispositifs dans lesquels le flux est produit par la chute de pression causée par la vitesse d'un autre fluide le fluide inducteur étant un fluide compressible déplaçant des fluides compressibles
F04D 29/42 - Carters d'enveloppeTubulures pour le fluide énergétique pour pompes radiales ou hélicocentrifuges
F04D 29/66 - Lutte contre la cavitation, les tourbillons, le bruit, les vibrations ou phénomènes analoguesÉquilibrage
F01D 11/00 - Prévention ou réduction des pertes internes du fluide énergétique, p. ex. entre étages
F01D 5/08 - Dispositifs de chauffage, de protection contre l'échauffement ou de refroidissement
F01D 5/06 - Rotors à plus d'un étage axial, p. ex. du type à tambour ou à disques multiplesLeurs parties constitutives, p. ex. arbres, connections des arbres
F02C 3/04 - Ensembles fonctionnels de turbines à gaz caractérisés par l'utilisation de produits de combustion comme fluide de travail ayant une turbine entraînant un compresseur
F16J 15/16 - Joints d'étanchéité entre deux surfaces mobiles l'une par rapport à l'autre
A folding yoke comprising a center yoke pivotally connected to separate foldable flexible yoke arms permits rotor blade fold about a single through bolt connection inboard of a set of bearings. In use, the compact folded arrangement of the rotor blades reduces folded aircraft dimensions in response to ever increasing restricted storage space parameters.
A folding rotor blade assembly for a tiltrotor aircraft comprising a rotor blade pivotally connected to a grip with dual concentric blade bolts having a common central axis providing a pivotal axis inboard of an outboard bearing. A folding spindle connects the outboard bearing to an outboard tip of a yoke. The outboard bearing and the spindle fold with the rotor blade relative to the yoke. In use, the compact folded arrangement of the rotor blades reduces folded aircraft dimensions in response to ever increasing restricted storage space parameters.
One example of a mount for a rotorcraft comprises a structural support member, a bracket, and an elastomer. The bracket is configured to attach to a component of the rotorcraft. The component of the rotorcraft produces vibrations at a first frequency. The structural support member configured to transfer a weight of the component of a rotorcraft to an airframe of the rotorcraft. A rotor system of the aircraft vibrates the airframe of the rotorcraft at a second frequency. The elastomer is located between a structural support member and a bracket. The elastomer is configured to attenuate noise caused by the vibrations at the first frequency by isolating the vibrations at the first frequency from reaching the airframe of the rotorcraft while the airframe vibrates at the second frequency.
A door system for a nacelle of a tiltrotor aircraft, the nacelle including a movable proprotor housing rotatable relative to a fixed portion of the nacelle from a forward flight mode to a vertical flight mode and a proprotor gearbox door connected to the movable proprotor housing and pivotably coupled to the fixed portion. The door system including a linkage to pivotably couple the door and the fixed portion of the nacelle; a track assembly mounted to the movable proprotor housing; and a door roller mechanism connected to the proprotor gearbox door. The door roller mechanism traverses the track assembly during rotation of the movable proprotor housing.
In one embodiment, a method may comprise heating a composite material into a viscous form, wherein the composite material comprises a thermoplastic and a plurality of reinforcement fibers, wherein the plurality of reinforcement fibers is randomly arranged within the thermoplastic. The method may further comprise extruding a plurality of strands of the composite material, wherein extruding the plurality of strands causes the plurality of reinforcement fibers within each strand to align. The method may further comprise arranging the plurality of strands of the composite material to form a mold tool, wherein the mold tool is configured to mold a composite structure at a heated temperature, and wherein the mold tool comprises an anisotropic thermal expansion property, wherein the anisotropic thermal expansion property is based on an orientation of the plurality of reinforcement fibers within the mold tool.
B29C 33/38 - Moules ou noyauxLeurs détails ou accessoires caractérisés par la matière ou le procédé de fabrication
B29C 33/40 - Matière plastique, p. ex. mousse ou caoutchouc
B29C 70/46 - Façonnage ou imprégnation par compression pour la fabrication d'objets de longueur définie, c.-à-d. d'objets distincts utilisant des moules opposables, p. ex. pour déformer des préimprégnés [SMC] ou des "prepregs"
B29C 70/20 - Façonnage de matières composites, c.-à-d. de matières plastiques comprenant des renforcements, des matières de remplissage ou des parties préformées, p. ex. des inserts comprenant uniquement des renforcements, p. ex. matières plastiques auto-renforçantes des renforcements fibreux uniquement caractérisées par la structure des renforcements fibreux utilisant des fibres de grande longueur, ou des fibres continues orientées dans une seule direction, p. ex. mèches ou autres fibres parallèles
B29C 70/88 - Façonnage de matières composites, c.-à-d. de matières plastiques comprenant des renforcements, des matières de remplissage ou des parties préformées, p. ex. des inserts caractérisées principalement par des propriétés spécifiques, p. ex. électriquement conductrices ou renforcées localement
B29C 48/18 - Articles comprenant au moins deux composants, p. ex. couches coextrudées les composants étant des couches
38.
Assembly fixture with anisotropic thermal properties
In one embodiment, a method may comprise heating a composite material into a viscous form, wherein the composite material comprises a thermoplastic and a plurality of reinforcement fibers, wherein the plurality of reinforcement fibers is randomly arranged within the thermoplastic. The method may further comprise extruding a plurality of strands of the composite material, wherein extruding the plurality of strands causes the plurality of reinforcement fibers within each strand to align. The method may further comprise arranging the plurality of strands of the composite material to form an assembly fixture, wherein the assembly fixture comprises an anisotropic thermal expansion property, and wherein the anisotropic thermal expansion property is based on an orientation of the plurality of reinforcement fibers within the assembly fixture.
B29C 41/02 - Façonnage par revêtement d'un moule, noyau ou autre support, c.-à-d. par dépôt de la matière à mouler et démoulage de l'objet forméAppareils à cet effet pour la fabrication d'objets de longueur définie, c.-à-d. d'objets séparés
B29C 48/05 - Moulage par extrusion, c.-à-d. en exprimant la matière à mouler dans une matrice ou une filière qui lui donne la forme désiréeAppareils à cet effet caractérisées par la forme à l’extrusion de la matière extrudée filamentaire, p. ex. fils
B29C 63/00 - Garnissage ou gainage, c.-à-d. application de couches ou de gainages préformés en matière plastiqueAppareils à cet effet
B29C 70/52 - Pultrusion, c.-à-d. façonnage et compression par traction continue à travers une matrice
B29C 64/118 - Procédés de fabrication additive n’utilisant que des matériaux liquides ou visqueux, p. ex. dépôt d’un cordon continu de matériau visqueux utilisant un matériau filamentaire mis en fusion, p. ex. modélisation par dépôt de fil en fusion [FDM]
B29C 33/38 - Moules ou noyauxLeurs détails ou accessoires caractérisés par la matière ou le procédé de fabrication
B29K 105/10 - Présentation, forme ou état de la matière moulée contenant des agents de renforcement, charges ou inserts de grande longueur, p. ex. ficelles, mèches, mats, tissus ou fils orientés
B29K 105/14 - Présentation, forme ou état de la matière moulée contenant des agents de renforcement, charges ou inserts de longueur réduite, p. ex. filaments coupés, fibres coupées ou crins orientés
A variable-speed gearbox for a tiltrotor with fixed engine and rotating proprotor includes an input shaft coupled to the respective fixed engine, an output shaft coupled to the respective proprotor; a high-speed clutch integrated into a high-speed gear train, the high-speed gear train having an input coupled to the input shaft and an output coupled to the output shaft; and a low-speed clutch integrated into a low-speed gear train, the low-speed gear train having an input coupled to the input shaft and an output coupled to the output shaft. The high-speed clutch and the low-speed clutch can be freewheeling clutches capable of disconnecting the output and the input of the respective gear train of the high and low-speed gear trains in an overrunning condition when the output rotates faster than the input of the respective gear train. The low-speed clutch can be permanently engaged. In accordance to some embodiments the variable-speed gearboxes may include an accessory drive.
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
B64C 27/28 - Giravions complexes, c.-à-d. aéronefs utilisant en vol à la fois les caractéristiques de l'avion et celles du giravion avec hélices propulsives de déplacement pouvant pivoter pour agir comme rotors de sustentation
B64C 27/52 - Basculement de l'ensemble du rotor par rapport au fuselage
F16H 3/08 - Transmissions à engrenages pour transmettre un mouvement rotatif à rapport de vitesse variable ou pour inverser le mouvement rotatif sans engrenages à mouvement orbital exclusivement ou principalement à engrenages constamment en prise, pouvant être libérés de leurs arbres
F16H 59/44 - Entrées de commande vers des transmissions transmettant un mouvement rotatif pour changements de vitesse ou pour mécanismes d'inversion les entrées étant fonction d'une vitesse fonction de la vitesse de la machine
F16H 3/24 - Transmissions à engrenages pour transmettre un mouvement rotatif à rapport de vitesse variable ou pour inverser le mouvement rotatif sans engrenages à mouvement orbital utilisant exclusivement ou principalement des engrenages qui peuvent être désengrenés par un déplacement selon l'axe uniquement et dont les arbres d'entraînement et entraînés sont coaxiaux
A bipendulum impact test machine for imparting impact damage includes a frame of beams where a weighted sled swings from a pair of links extending from a carriage. The carriage and sled are vertically adjustable along a set of vertical shafts of the frame. The sled is permanently horizontally oriented and parallel with the carriage. Interchangeable impact tips are removably and adjustably engaged with the sled. The impact tips have a variety of shapes in order to simulate different impact scenarios. The device is mobile and capable of imparting impact damage to large aircraft parts even in an installed condition.
G01N 3/48 - Recherche de la dureté ou de la dureté au rebondissement en effectuant des empreintes sous une charge impulsive par des dispositifs de pénétration, p. ex. chute d'une bille
G01N 3/303 - Recherche des propriétés mécaniques des matériaux solides par application d'une contrainte mécanique en appliquant une force unique et brève engendrée uniquement par un poids en chute libre
41.
METHODS OF MAKING A SPECIMEN WITH A PREDETERMINED WRINKLE DEFECT
In a first aspect, there is a method of making a specimen with a predetermined wrinkle defect, the steps including orienting a composite material around a layup tool at a wrap angle to form a closed loop; and generating at least one wrinkle with a predetermined characteristic in a portion of the closed loop to form a specimen. The predetermined characteristic is at least one of the following: wrinkle location, an outward wrinkle, an inward wrinkle, a wrinkle width, a wrinkle height, and a wrinkle length. In another aspect, there is a method of determining allowable defects for a composite component.
B29C 70/32 - Façonnage par empilage, c.-à-d. application de fibres, de bandes ou de feuilles larges sur un moule, un gabarit ou un noyauFaçonnage par pistolage, c.-à-d. pulvérisation de fibres sur un moule, un gabarit ou un noyau sur un moule, un gabarit ou un noyau rotatifs
An embodiment fluid recovery structure includes a body having an interior cavity, ports integrally joined to first walls of the body and having port walls that extend away from the body, with each of the ports having a port opening that is contiguous with the interior cavity, and a drain structure integrally joined to a second wall of the body and having a drain hole that extends from the interior cavity through the drain structure.
F16L 55/168 - Dispositifs pour aveugler les fuites dans les tuyaux ou manches à partir de l'extérieur du tuyau
B64D 37/00 - Aménagements relatifs à l'alimentation des groupes moteurs en carburant
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
F16L 55/07 - Aménagement ou montage de dispositifs, p. ex. soupapes, pour ventiler ou aérer ou purger
F16L 23/16 - Raccords à brides caractérisés par les moyens d'étanchéité
B64C 1/14 - FenêtresPortesTrappes d'évacuation ou panneaux de visiteStructures de cadres environnantsVerrièresPare-brise
F02M 25/08 - Appareils spécifiques conjugués aux moteurs pour ajouter des substances non combustibles ou de petites quantités de combustible secondaire, à l’air comburant, au combustible principal ou au mélange air-combustible ajoutant des vapeurs combustibles aspirées des réservoirs de combustible du moteur
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 27/82 - GiravionsRotors 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
F02M 37/00 - Appareils ou systèmes pour transférer le combustible liquide des réservoirs de stockage aux carburateurs ou aux injecteursDispositions d'épuration du combustible liquide spécialement conçues pour les moteurs à combustion interne ou aménagées sur ceux-ci
An aircraft including a nacelle disposed at a fixed location relative a wing member; a proprotor housing coupled to the nacelle, the proprotor housing configured to selectively rotate between a horizontal orientation and a non-horizontal orientation; a door pivotably coupled to the proprotor housing; and a linkage to connect the door and the nacelle, the linkage configured to move with the door from a closed position when the proprotor housing is in a horizontal orientation to an open position when the proprotor housing is in a non-horizontal orientation. In some embodiments, there can be a hinge member for hingedly coupling the door to the proprotor and/or nacelle. In other embodiments, the door includes a flexure portion. In some embodiments, the nacelle includes a plurality of doors. In other embodiments, proprotor includes a forward portion and a stationary aft portion; wherein the forward portion is configured to selectively pivot.
A system and algorithm-based method of determining engine health and assuring available propulsion power based on historical data reflecting the individual engine's unique performance “fingerprint.”
G06F 7/08 - Tri, c.-à-d. rangement des supports d'enregistrement dans un ordre de succession numérique ou autre, selon la classification d'au moins certaines informations portées sur les supports
G07C 5/00 - Enregistrement ou indication du fonctionnement de véhicules
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
B64D 45/00 - Indicateurs ou dispositifs de protection d'aéronefs, non prévus ailleurs
A rotorcraft, such a helicopter or a tiltrotor aircraft, includes a light emitting device configured to provide light at a tip of a rotor blade. The light emitting device includes a light emitting diode arranged on the rotor blade, and a power source, wherein the power source is configured to power the light emitting diode due to a movement of the rotor blade. The power source may include a piezo-electric material configured to create a voltage due to movements of the rotor blade or an electrical generator including a stationary magnet assembly and a moveable coil assembly arranged on a shaft that rotates the rotor blade.
One embodiment of the present invention is a method for automatically reducing the effect of a component of an external force that is laterally incident on a rotorcraft. A signal of the rotorcraft indicative of and proportional to the component is monitored. An absolute value of the signal and a preset high limit are compared. If the absolute value is greater than the preset high limit, manual heading control of the rotorcraft is disabled and the heading of the rotorcraft is adjusted with respect to the external force so as to decrease the lateral component of the external force experienced by the rotorcraft.
A system for detecting position that is capable of self-monitoring for connectivity faults. In one embodiment, the system comprises a transformer, an excitation potential source, a bias potential source, and a processor.
G01B 7/14 - Dispositions pour la mesure caractérisées par l'utilisation de techniques électriques ou magnétiques pour mesurer la distance ou la marge entre des objets ou des ouvertures espacés
G01B 7/00 - Dispositions pour la mesure caractérisées par l'utilisation de techniques électriques ou magnétiques
G01B 7/30 - Dispositions pour la mesure caractérisées par l'utilisation de techniques électriques ou magnétiques pour mesurer des angles ou des cônesDispositions pour la mesure caractérisées par l'utilisation de techniques électriques ou magnétiques pour tester l'alignement des axes
48.
Strained capable conductive/resistive composite hybrid heater for thermal anti-ice device
A rotor blade of a helicopter is presented. In an embodiment, the rotor blade includes a body; and a heating mat arranged in the body and configured to supply heat to said body. The heating mat includes a first plurality of fibers and a second plurality of fibers electrically connected to the first plurality of fibers. The first plurality of fibers define a positive angle smaller than about +45° relative to a first direction perpendicular to a longitudinal direction of the body. The second plurality of fibers define a negative angle greater than about −45° relative to the first direction.
A flow control device is disclosed including a flow control surface over which fluid is designed to flow in a predetermined direction. Vortex generators are associated with the flow control surface. Each respective vortex generator has a pivot axis that forms an acute angle with respect to the predetermined direction and is capable of being positioned in both of an extended state, in which the respective vortex generators function to create a swirling fluid flow, and a retracted state, in which the respective vortex generators are pivoted via the pivot axis so as to lie adjacent to the flow control surface. An actuator is associated with each of the vortex generators, each actuator adapted to position the associated vortex generator between the extended and retracted states. The flow control device is disclosed to be used in tiltrotor vehicles.
A power situation indicator configured to provide power information in a rotorcraft is presented. The power situation indicator includes a detection unit configured to detect a current value of each of a plurality of control parameters, each of the plurality of control parameters including a pre-determined operating limit; a calculation unit configured to normalize on a common power scale (a) the current value and (b) the pre-determined operating limit of each of the plurality of control parameters, and a display unit configured to dynamically display on the common power scale a first moveable indicator and a second moveable indicator. The first moveable indicator is driven by one of the plurality of control parameters having the highest normalized current value and the second moveable indicator is driven by one of the plurality of control parameters having its normalized current value that is the closest to its corresponding normalized pre-determined operating limit.
An assembly for providing flexure to a blade of a rotary blade system, the assembly including an upper support plate having an upper curved surface, a lower support plate having a lower curved surface, and a yoke positioned therebetween. At least one of the upper and lower yoke surfaces having a layer of cushioning material positioned thereon and secured thereto. The layer of cushioning material extending along and following the general contour of yoke surface, and the layer of cushioning material directly contacting a support plate. Another embodiment is an assembly for providing flexure to a blade of a rotary blade system, including, an upper support plate having an upper curved surface, a lower support plate having a lower curved surface, and a yoke positioned therebetween and directly contacting the support plates wherein one of the curved surfaces is a non-circular arc that does not form part of the circumference of a circle.
B63H 1/06 - Éléments de propulsion agissant directement sur l'eau de type rotatif à axe de rotation essentiellement disposé à angle droit par rapport à la direction de propulsion, p. ex. roues à aubes à aubes ou pales réglables
A torsionally de-coupled engine mount system (13) for use in tilt rotor aircraft (11) applications is disclosed, in which an engine is mounted at its forward end to a prop rotor gear box by means of a forward mount (303) that is a simple adapter fitting, and at its aft end to a pylon assembly by an aft mount (305) that is a simple bi-pod fitting. The forward mount (303) counteracts forces and moments in six degrees of freedom, but the aft mount (305) only counteracts lateral and vertical loads. The contribution from the engine to the overall dynamic response of the aircraft is tuned by selectively tailoring the size, shape, weight, and material of the forward mount (303). The engine mount system torsionally de-couples the engines from the prop rotors, thereby preventing rotor torque from being induced into the engines. In addition, the contribution from the engines to the overall dynamic response of the aircraft can be tuned by selectively tailoring the size, shape, weight, and material of the forward mounts between the engines and the transmissions.
brevets
