A rotor system is provided in one example embodiment and may include a rotor duct; at least one rotor blade, wherein the at least one rotor blade comprises a tip end; and a multi-material tip extension affixed at the tip end of the at least one rotor blade, wherein the multi-material tip extension comprises an inboard portion fabricated from a first material and an outboard portion fabricated from a second material, wherein the second material is different than the first material.
One embodiment is a bearing carrier assembly including a circular shield having top and bottom surfaces; and a number of bearing separators integrated with the bottom surface of the shield, wherein each pair of bearing separators defines a receptacle for receiving and retaining a bearing therewithin and wherein the shield blocks the received bearings from debris and retains lubricant around the received bearings. Each of the bearing separators may include a spacer element for separating adjacent ones of the bearings. The bearing carrier assembly may be made up of a number of carrier sections that interconnect to form the bearing carrier assembly.
F16C 33/41 - Cages à billes comportant une bague portant des doigts de séparation des éléments de roulement
F16C 19/16 - Paliers à contact de roulement pour mouvement de rotation exclusivement avec roulements à billes essentiellement du même calibre, en une ou plusieurs rangées circulaires pour charges à la fois radiales et axiales avec une seule rangée de billes
B64F 5/10 - Fabrication ou assemblage d’aéronefs, p. ex. gabarits à cet effet
B64C 27/20 - Giravions caractérisés par le fait qu'ils possèdent des rotors haubanés, p. ex. plates-formes volantes
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]
6.
Assembly fixture with anisotropic thermal properties
In one embodiment, an assembly fixture may include a base structure including a plurality of strands of a fiber-reinforced thermoplastic material comprising a thermoplastic embedded with a plurality of reinforcement fibers, wherein the plurality of reinforcement fibers is aligned within each strand of the plurality of strands, and wherein the base structure further comprises an anisotropic thermal expansion property based on an orientation of the plurality of reinforcement fibers within the base structure, The assembly fixture may further include a plurality of fastening structures coupled to the base structure, wherein the plurality of fastening structures is configured to fasten a plurality of components of a composite structure for assembly using a heated bonding process.
B29C 65/00 - Assemblage d'éléments préformésAppareils à cet effet
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
B64F 5/10 - Fabrication ou assemblage d’aéronefs, p. ex. gabarits à cet effet
B29C 65/78 - Moyens pour la manipulation des éléments à assembler, p. ex. pour la fabrication de récipients ou d'objets creux
B29C 70/54 - Parties constitutives, détails ou accessoiresOpérations auxiliaires
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
In some examples, an aircraft comprises a motorized module. The motorized module comprises a motor and a first coil. The motor is to operate equipment onboard the aircraft and generates vibrations during operation. The first coil is operable to wirelessly transmit power to a separate module onboard the aircraft based on electromagnetic induction between the first coil and a second coil in a separate module, and wirelessly transfer data with the separate module via the second coil based on the electromagnetic induction, the data being associated with the motor. A gap separates the motorized module and the separate module. The gap isolates the separate module from the vibrations.
B64D 31/14 - Transmissions entre les dispositifs d'amorçage de la commande et les groupes moteurs
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
H02J 50/10 - Circuits ou systèmes pour l'alimentation ou la distribution sans fil d'énergie électrique utilisant un couplage inductif
B64C 39/02 - Aéronefs non prévus ailleurs caractérisés par un emploi spécial
8.
Method for generating a simulation model to evaluate aircraft flight systems
A method for generating a simulation model to evaluate a flight control system including determining at least one high level requirement for an aircraft flight system during a non-automated engineering process; generating at least one specification of the high level requirement; generating a model computer-readable program code based on the at least one specification; executing the model computer-readable program code to generate a model code unit; executing the model code unit to generate a procedure document; executing the model code unit to perform a simulation method to generate a bench test computer-readable program code: executing the bench test computer-readable program code on a bench test computing device to generate a simulation output; and comparing the simulation output to the at least one specification of the high level requirement to generate a pass or fail result.
G06F 30/20 - Optimisation, vérification ou simulation de l’objet conçu
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
An apparatus is described and in one embodiment includes a first portion comprising an inner diameter, a first outer diameter, and a first length and a second portion, wherein the first portion and the second portion are integrally connected together, the second portion comprising the inner diameter, at least one second outer diameter, and a second length. The embodiment further includes a flange comprising a contact surface, wherein the inner diameter of the first portion and the second portion provides a hollow pathway through the apparatus.
F16M 13/02 - Autres supports ou appuis pour positionner les appareils ou les objetsMoyens pour maintenir en position les appareils ou objets tenus à la main pour être portés par un autre objet ou lui être fixé, p. ex. à un arbre, une grille, un châssis de fenêtre, une bicyclette
G01L 19/00 - Détails ou accessoires des appareils pour la mesure de la pression permanente ou quasi permanente d'un milieu fluent dans la mesure où ces détails ou accessoires ne sont pas particuliers à des types particuliers de manomètres
12.
System and method for selectively modulating the flow of bleed air used for high pressure turbine stage cooling in a power turbine engine
A method for selectively modulating bleed air used for cooling a downstream turbine section in a gas turbine engine. The method including: measuring an engine and/or aircraft performance parameter by an engine sensor device; comparing the engine and/or aircraft performance parameter to a performance threshold; determining a bleed trigger condition, if the engine and/or aircraft performance parameter crosses the performance threshold; determining a non-cooling condition, if the engine and/or aircraft performance parameter is below the performance threshold; actuating a flow control valve to an open position, in response to the bleed trigger condition, so that bleed air is extracted from the compressor section and flowed to the downstream turbine section; and terminating, in response to the non-cooling condition, the flow of the bleed air to the downstream turbine section of the engine by actuating the flow control valve to a closed position.
F02C 9/18 - Commande du débit du fluide de travail par prélèvement, par bipasse ou par action sur des raccordements variables du fluide de travail entre des turbines ou des compresseurs ou entre leurs étages
F01D 17/04 - Aménagement des éléments sensibles sensibles à la charge
F01D 17/06 - Aménagement des éléments sensibles sensibles à la vitesse
F01D 17/08 - Aménagement des éléments sensibles sensibles aux conditions de fonctionnement du fluide énergétique, p. ex. à la pression
F02C 6/08 - Ensembles fonctionnels de turbines à gaz délivrant un fluide de travail chauffé ou pressurisé à d'autres appareils, p. ex. sans sortie de puissance mécanique délivrant des gaz comprimés le gaz étant prélevés sur le compresseur de la turbine à gaz
B64F 5/60 - Test ou inspection des composants ou des systèmes d'aéronefs
B64D 33/08 - Aménagement sur les aéronefs des éléments ou des auxiliaires des ensembles fonctionnels de propulsion, non prévu ailleurs des systèmes de refroidissement des ensembles fonctionnels de propulsion
One embodiment is a system comprising fuel tank comprising a pressure vessel for storing fuel for a vehicle, the fuel tank disposed within a fuselage of the vehicle and extending a majority of a length of the fuselage, wherein a center of gravity of the fuel tank is substantially aligned with a center of gravity of the fuselage. The fuel tank may be disposed within the fuselage such that the fuel tank bears at least a portion of a load borne by the fuselage. Alternatively, the fuel tank may be disposed within the fuselage such that the fuel tank is isolated from loads borne by the fuselage. In certain embodiments, the fuel tank comprises a filament wound pressure vessel.
A system for image guided assembly of a structure, the structure defining an interior area accessible through at least one access opening, the interior area including at least one fastener hole. The system including a first fastening tool including an arm with first and second ends; and a support plate on the first end, the support plate including at least one connection member to securely retain a fastener therein, the at least one connection member configured to facilitate alignment of the fastener with the at least one fastener hole; an image capturing device disposed on the arm first end configured to generate a captured image of the interior area; a light source associated with the arm first end, the light source configured to generate light at the first end of the arm; and a display device located outside the interior area for displaying the captured image of the interior area.
B25B 23/18 - Dispositifs pour illuminer la tête d'une vis ou d'un écrou
B23Q 17/24 - Agencements sur les machines-outils pour indiquer ou mesurer utilisant des moyens optiques
B64F 5/10 - Fabrication ou assemblage d’aéronefs, p. ex. gabarits à cet effet
B25B 23/10 - Dispositions pour manipuler les vis ou écrous pour tenir ou présenter la vis ou l'écrou avant ou pendant sa rotation par des moyens mécaniques de prise
B25J 1/04 - Manipulateurs mus dans l'espace manuellement rigides, p. ex. pour atteindre des rayonnages
B33Y 80/00 - Produits obtenus par fabrication additive
Various implementation described herein are directed to a method for identifying a blockage in a pitot-static system. A pressure signal is received. Pressure fluctuations in the pressure signal are identified. A determination is made as to whether a blockage has occurred in the pitot-static system based on the identified pressure fluctuations.
G01P 21/02 - Essai ou étalonnage d'appareils ou de dispositifs couverts par les autres groupes de la présente sous-classe de tachymètres
G01P 5/16 - Mesure de la vitesse des fluides, p. ex. d'un courant atmosphériqueMesure de la vitesse de corps, p. ex. navires, aéronefs, par rapport à des fluides en mesurant les différences de pression dans le fluide en utilisant des tubes de Pitot
16.
Active airflow management for tiltrotor hub thermal ventilation
Embodiments are directed to an aerodynamic spinner fairing having a sidewall and one or more airflow intakes in the sidewall. The airflow intakes are closed during a first phase of flight and open during a second phase of flight. The first phase of flight may be an airplane mode for a tiltrotor aircraft, and the second phase of flight may be a helicopter mode for the tiltrotor aircraft. The airflow intakes may comprise an opening in the sidewall, and a door that is configured to move between a first position covering the opening and a second position exposing the opening to external airflow. An actuator coupled to the door may operate to move the door between the first position and the second position. One or more guide vanes within the aerodynamic spinner fairing may be configured to direct air received via the airflow intakes to provide convection cooling.
B64C 23/00 - Moyens permettant d'influencer l'écoulement d'air sur les surfaces des aéronefs, non prévus ailleurs
B64C 27/28 - Giravions complexes, c.-à-d. aéronefs utilisant en vol à la fois les caractéristiques de l'avion et celles du giravion avec hélices propulsives de déplacement pouvant pivoter pour agir comme rotors de sustentation
B64C 29/00 - Aéronefs capables d'atterrir ou de décoller à la verticale, p. ex. aéronefs à décollage et atterrissage verticaux [ADAV, en anglais VTOL]
A method of selectively preventing flapping of a rotor hub includes providing a flapping lock proximate to a rotor hub and shaft assembly and moving the flapping lock from an unlocked position to a locked position, the flapping lock operable in the locked position to prevent at least some flapping movement of the rotor hub relative to the shaft, the flapping lock operable in the unlocked position to allow the at least some flapping movement of the rotor hub relative to the shaft.
B64C 27/41 - Rotors comportant des articulations l'articulation de battement ou le joint universel étant commun à l'ensemble des pales
B64C 27/30 - Giravions complexes, c.-à-d. aéronefs utilisant en vol à la fois les caractéristiques de l'avion et celles du giravion avec moyens permettant de réduire la traînée du rotor en période de non fonctionnement
B64C 27/50 - Pales repliables pour faciliter le rangement de l'aéronef
B64C 27/52 - Basculement de l'ensemble du rotor par rapport au fuselage
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 29/00 - Aéronefs capables d'atterrir ou de décoller à la verticale, p. ex. aéronefs à décollage et atterrissage verticaux [ADAV, en anglais VTOL]
B64C 27/615 - Transmissions, p. ex. en liaison avec les moyens déclenchant ou agissant sur les pales mécaniques comportant des volets montés sur les pales
18.
Electrical load shed to increase available aircraft power
Embodiments are directed to systems and methods for managing electrical load in an aircraft comprising a generator coupled to an aircraft engine, and a power distribution controller configured to monitor current engine operating parameters and to reduce an electrical load on the generator when the engine operating parameters reach a limit during specified aircraft operating conditions. The system may further comprise a non-essential electrical bus coupled to the generator, wherein the electrical load on the generator is reduced by disconnecting the non-essential bus from the generator. The generator may be coupled to the aircraft engine via an accessory gearbox or a transmission gearbox. The monitored current engine operating parameters comprise one or more of an engine torque, a gas generator RPM, and a temperature. The aircraft operating conditions may comprise one or more of a takeoff, a landing, or an engine failure.
B64D 41/00 - Installations génératrices de puissance pour servitudes auxiliaires
B60R 16/03 - Circuits électriques ou circuits de fluides spécialement adaptés aux véhicules et non prévus ailleursAgencement des éléments des circuits électriques ou des circuits de fluides spécialement adapté aux véhicules et non prévu ailleurs électriques pour l'alimentation des sous-systèmes du véhicule en énergie électrique
H02B 1/20 - Schémas de barres omnibus ou d'autres fileries, p. ex. dans des armoires, dans les stations de commutation
An aircraft includes a first rotor assembly, a second rotor assembly, and a rotor phase angle control system. The system includes a phase adjustor operably associated with the first rotor assembly and the second rotor assembly. The method includes sensing vibrations exerted on the aircraft and offsetting a phase angle of the first rotor assembly and the second rotor assembly to minimize the vibrations.
B64C 11/50 - Synchronisation des hélices multiples
G10K 11/178 - Procédés ou dispositifs de protection contre le bruit ou les autres ondes acoustiques ou pour amortir ceux-ci, en général utilisant des effets d'interférenceMasquage du son par régénération électro-acoustique en opposition de phase des ondes acoustiques originales
B64C 27/30 - Giravions complexes, c.-à-d. aéronefs utilisant en vol à la fois les caractéristiques de l'avion et celles du giravion avec moyens permettant de réduire la traînée du rotor en période de non fonctionnement
A notch treatment method for flaw simulation including providing the specimen with the notch, the notch having a re-melt material layer; isolating the notch; and selectively etching the notch to provide an etched surface of the notch; wherein at least a portion of the re-melt material layer has been removed from the notch. In one aspect, there is provided a notch treatment method for flaw simulation including providing the specimen with the notch, the notch having a re-melt material layer, the specimen includes steel or an alloy thereof; isolating the notch; and selectively etching the notch with a first etching solution and a second etching solution to provide an etched surface on the notch; wherein at least a portion of the re-melt material layer has been removed from the notch.
A material dispensing system including a first frame and a first application head. The first application head supported by the first frame including a first bias ply assembly comprising a bias ply roll supported on a bias ply dispenser unit, the first bias ply assembly configured to pass bias ply material along a bias path; and a first non-bias ply assembly comprising a non-bias ply roll supported by a non-bias ply dispenser unit, the non-bias ply assembly configured to pass non-bias ply material along a non-bias path; wherein the bias path and the non-bias path are substantially parallel. Another aspect provides a material dispensing system including a first frame and a first application head supported thereby; and a second frame and a second application head supported thereby; wherein the first frame and the second frame move in an X direction during operation. Another aspect includes preparing a composite article.
B29C 70/38 - Empilage automatisé, p. ex. utilisant des robots, par application de filaments selon des modèles prédéterminés
B29C 70/34 - 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 et façonnage ou imprégnation par compression
B64F 5/10 - Fabrication ou assemblage d’aéronefs, p. ex. gabarits à cet effet
A system for monitoring lubrication of a drive train, including a lubricant pressure sensor to detect a pressure of the lubricant in the drive train and to provide a lubricant pressure signal; lubricant volume sensor to detect a volume of the lubricant in the drive train and to provide a lubricant volume signal; non-contact temperature sensor to detect a temperature of the drive train and to provide a non-contact temperature signal; and logic management system in communication with the lubricant pressure sensor, the lubricant volume sensor, and the non-contact temperature sensor; the logic management system configured to receive and process the lubricant pressure signal, the lubricant volume signal, and the non-contact temperature signal; wherein when the lubricant pressure signal reaches a predetermined minimum pressure level and the lubricant volume signal reaches a predetermined minimum volume level, the logic management system displays non-contact temperature measurement data to a display device.
F16H 57/04 - Caractéristiques relatives à la lubrification ou au refroidissement
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
G07C 5/12 - 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 sous forme de graphique
B64D 43/00 - Aménagements ou adaptations des instruments
B64D 45/00 - Indicateurs ou dispositifs de protection d'aéronefs, non prévus ailleurs
G05D 1/00 - Commande de la position, du cap, de l'altitude ou de l'attitude des véhicules terrestres, aquatiques, aériens ou spatiaux, p. ex. utilisant des pilotes automatiques
G05D 1/08 - Commande de l'attitude, c. à d. élimination ou réduction des effets du roulis, du tangage ou des embardées
G05D 3/00 - Commande de la position ou de la direction
G06F 7/00 - Procédés ou dispositions pour le traitement de données en agissant sur l'ordre ou le contenu des données maniées
G06F 17/00 - Équipement ou méthodes de traitement de données ou de calcul numérique, spécialement adaptés à des fonctions spécifiques
G06F 7/70 - Méthodes ou dispositions pour effectuer des calculs en utilisant une représentation numérique non codée, c.-à-d. une représentation de nombres sans baseDispositifs de calcul utilisant une combinaison de représentations de nombres codées et non codées utilisant des trains d'impulsions stochastiques, c.-à-d. des impulsions apparaissant au hasard et dont la moyenne des taux d'impulsion représente des nombres
G06G 7/00 - Dispositifs dans lesquels l'opération de calcul est effectuée en faisant varier des grandeurs électriques ou magnétiques
G06G 7/76 - Calculateurs analogiques pour des procédés, des systèmes ou des dispositifs spécifiques, p. ex. simulateurs de circulation, p. ex. circulation routière
In one embodiment, a rotor hub comprises a yoke for attaching a plurality of rotor blades, a constant velocity joint to drive torque from a mast to the yoke and to enable the yoke to pivot, and a rotor control system configured to adjust an orientation of the plurality of rotor blades. Moreover, the rotor control system comprises: a swashplate, an adapter ring, a plurality of actuators controlled based on a flight control input, a plurality of lower pitch links configured to transfer motion between the swashplate and the adapter ring, a plurality of phase adjustment levers configured to adjust a control phase associated with motion transferred between the swashplate and the adapter ring, and a plurality of upper pitch links configured to adjust a pitch of the plurality of rotor blades, wherein there are more upper pitch links than lower pitch links.
B64C 27/33 - Rotors comportant des bras qui peuvent fléchir
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 29/00 - Aéronefs capables d'atterrir ou de décoller à la verticale, p. ex. aéronefs à décollage et atterrissage verticaux [ADAV, en anglais VTOL]
A fairing is provided in one example embodiment and may include an apparatus to receive at least one of a foot traffic load and a hand traffic load, wherein the apparatus can include: a step portion that is to receive at least a portion of the foot traffic load; a handhold portion that is to receive at least a portion of the hand traffic load, wherein the handhold portion extends downward from the step portion; and a support structure, wherein the support structure extends downward from of the step portion. The apparatus can include an outer flange attached to the fairing. At least a portion of the step portion the apparatus can be recessed within the fairing at a distance between one inch and three inches from a top surface of the fairing. The handhold portion can include one or more drain holes.
Methods and systems for automated placement of composite material on a surface of a component, the composite material including unidirectional fibers, is provided. A set of fiber paths along the surface is established, the set of fiber paths comprising at least one ply, each ply comprising a respective plurality of fiber paths being substantially aligned with a respective direction. An isotropy factor for the component is determined based on the set of fiber paths, the isotropy factor being indicative of a distribution of the plurality of fiber paths on the surface. When the isotropy factor exceeds a predetermined threshold, a respective layer of composite material is applied to the surface of the component using an automated fiber placement machine and for each of the at least one ply, wherein the unidirectional fibers of the composite material are applied along the set of fiber paths.
B29C 70/38 - Empilage automatisé, p. ex. utilisant des robots, par application de filaments selon des modèles prédéterminés
B32B 5/12 - Produits stratifiés caractérisés par l'hétérogénéité ou la structure physique d'une des couches caractérisés par les caractéristiques de structure d'une couche comprenant des fibres ou des filaments caractérisés par la disposition relative des fibres ou filaments des couches adjacentes
B32B 37/00 - Procédés ou dispositifs pour la stratification, p. ex. par polymérisation ou par liaison à l'aide d'ultrasons
B32B 41/00 - Dispositions pour le contrôle ou la commande des procédés de stratificationDispositions de sécurité
An embodiment of the present invention provides a blocking door that is pivotally disposed on a fixed nacelle of a tiltrotor aircraft for pivoting between a stowed position when a proprotor pylon is in the substantially horizontal position and a protective blocking position in front of the proprotor pylon when the proprotor pylon is positioned in the non-horizontal position. In other aspects, there is provided a blocking door and a method of reducing infrared and/or radar signatures of rotorcraft with a rotatable proprotor.
B64D 29/06 - Fixation des nacelles, carénages ou capotages
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
F41H 3/00 - Camouflage, c.-à-d. moyens ou procédés de dissimulation ou de simulation
28.
Methods and systems for manufacturing composite components
A method for forming composite components includes disposing composite laminate over a mandrel. The method further includes infusing the composite laminate with a resin. A gelation of the infused resin is caused by applying a first environmental condition to the composite laminate and mandrel. At least a portion of the mandrel is deformed by applying a second environmental condition to the composite laminate and mandrel. The method further includes forming a composite structure by curing the composite laminate infused with resin. The deformed mandrel is removed from the composite structure after forming the composite structure.
B29C 64/00 - Fabrication additive, c.-à-d. fabrication d’objets en trois dimensions [3D] par dépôt additif, agglomération additive ou stratification additive, p. ex. par impression en 3D, stéréolithographie ou frittage laser sélectif
B29C 33/38 - Moules ou noyauxLeurs détails ou accessoires caractérisés par la matière ou le procédé de fabrication
B29C 33/44 - Moules ou noyauxLeurs détails ou accessoires comportant des moyens ou conçus spécialement pour faciliter le démoulage d'objets, p. ex. des objets à contre-dépouille
B29C 35/02 - Chauffage ou durcissement, p. ex. réticulation ou vulcanisation
B29C 70/44 - Façonnage ou imprégnation par compression pour la fabrication d'objets de longueur définie, c.-à-d. d'objets distincts utilisant une pression isostatique, p. ex. moulage par différence de pression, avec un sac à vide, dans un autoclave ou avec un caoutchouc expansible
B29C 70/48 - 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" avec une imprégnation des renforcements dans le moule fermé, p. ex. moulage par transfert de résine [RTM]
B29L 31/30 - Véhicules, p. ex. bateaux ou avions, ou éléments de leur carrosserie
A light weight hybrid torque transfer joint trunnion has an integral metal hub spline fitting oriented on a center axis. This integral metal hub spline fitting may be made of steel, aluminum, titanium, or the like and may be generally cylindrical. The integral metal hub spline fitting defines an integral central internally-splined mast or driveshaft coupling opening centered about the center axis. A composite material body centrally retains, and is cured to, the metal hub spline fitting. Torque transfer joint link attachment pins extend from the composite material body and are rigidly linked to the metal hub spline fitting. In an example constant-velocity joint, a plurality of pivoting linkages may each be rotatably coupled to the torque transfer joint link attachment pins, and each of the plurality of pivoting linkages may, in turn be secured to a rotor yoke configured to mount a plurality of rotorcraft blades.
F16D 3/60 - Accouplements extensibles, c.-à-d. avec moyens permettant le mouvement entre parties accouplées durant leur entraînement avec pièces d'accouplement reliées par un ou plusieurs organes intermédiaires comportant des tringles de poussée ou de traction reliées à la fois aux deux parties
F16D 1/10 - Accouplements à action rapide dans lesquels les pièces sont simplement présentées dans l'axe
B64F 5/10 - Fabrication ou assemblage d’aéronefs, p. ex. gabarits à cet effet
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]
B29C 70/84 - Moulage de matière sur des parties préformées à réunir
B22D 25/02 - Coulée particulière caractérisée par la nature du produit par sa formeCoulée particulière caractérisée par la nature du produit d'œuvres d'art
B29K 705/00 - Utilisation de métaux, leurs alliages ou leurs composés pour des pièces préformées, p. ex. pour des inserts
A radial inlet plenum a forward panel, an aft panel, and a cowling extending therebetween. The forward and aft panels are coupled between the cowling and an engine. The forward and aft panels include flexible sections to allow the engine to translate radially and axially, as well as rotate, relative to the cowling.
B64D 33/02 - Aménagement sur les aéronefs des éléments ou des auxiliaires des ensembles fonctionnels de propulsion, non prévu ailleurs des entrées d'air de combustion
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
31.
Adaptable rotor control system for a variable number of blades
In one embodiment, a rotor hub comprises a yoke for attaching a plurality of rotor blades, a constant velocity joint to drive torque from a mast to the yoke and to enable the yoke to pivot, and a rotor control system configured to adjust an orientation of the plurality of rotor blades. Moreover, the rotor control system comprises: a swashplate, a phase adapter fulcrum, a plurality of actuators controlled based on a flight control input, a plurality of lower pitch links configured to transfer motion between the plurality of actuators and the swashplate, a plurality of phase adjustment levers configured to adjust a control phase associated with motion transferred between the plurality of actuators and the plurality of lower pitch links, and a plurality of upper pitch links configured to adjust a pitch of the plurality of rotor blades, wherein there are more upper pitch links than lower pitch links.
B64C 11/06 - Montage des pales dans le cas de pales à pas variable
B64C 11/32 - Mécanismes de changement de pas des pales mécaniques
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 11/30 - Mécanismes de changement de pas des pales
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 cyclic stick for transmitting control commands to blades of a rotorcraft via at least one transmission member, including a grip configured for engagement with a pilot's hand, a control arm and at least one locking mechanism. The control arm has a bottom end configured for connection to the transmission member(s) and for rotational connection to a base support structure, and a top end pivotally connected to the grip. The control arm includes first and second arm portions pivotally connected to each other, the first arm portion defining the bottom end, the second arm portion defining the top end. The locking mechanism(s) selectively prevent a relative pivoting motion between the first and second arm portions and a relative pivoting motion between the second arm portion and the grip. A method of adjusting a position of a grip of a cyclic stick in a rotorcraft cabin is also discussed.
B64C 13/06 - Dispositifs amorçant la mise en œuvre actionnés par l'homme réglables pour s'adapter à la conformation de l'utilisateur
B64C 13/04 - Dispositifs amorçant la mise en œuvre actionnés par l'homme
B64C 27/56 - 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
G05G 9/047 - Mécanismes de commande manuelle équipés d'un seul organe de commande travaillant avec plusieurs organes commandés, p. ex. en sélection ou simultanément l'organe de commande étant manœuvré de différentes manières indépendantes, chacune de ces manœuvres individuelles entraînant un seul organe commandé dans lesquels la manœuvre de l'organe de commande peut être effectuée de plusieurs manières simultanément l'organe de commande étant manœuvré à la main autour d'axes orthogonaux, p. ex. manches à balai
B64C 13/14 - Dispositifs amorçant la mise en œuvre actionnés par l'homme blocables
A cyclic stick for transmitting control commands to blades of a rotorcraft via at least one transmission member, including a grip configured for engagement with a pilot's hand, a control arm and at least one locking mechanism. The control arm has a bottom end configured for connection to the transmission member(s) and for rotational connection to a base support structure, and a top end pivotally connected to the grip. The control arm includes first and second arm portions pivotally connected to each other, the first arm portion defining the bottom end, the second arm portion defining the top end. The locking mechanism(s) selectively prevent a relative pivoting motion between the first and second arm portions and a relative pivoting motion between the second arm portion and the grip. A method of adjusting a position of a grip of a cyclic stick in a rotorcraft cabin is also discussed.
A cyclic stick for transmitting control commands to blades of a rotorcraft via at least one transmission member, including a grip configured for engagement with a pilot's hand, a control arm and at least one locking mechanism. The control arm has a bottom end configured for connection to the transmission member(s) and for rotational connection to a base support structure, and a top end pivotally connected to the grip. The control arm includes first and second arm portions pivotally connected to each other, the first arm portion defining the bottom end, the second arm portion defining the top end. The locking mechanism(s) selectively prevent a relative pivoting motion between the first and second arm portions and a relative pivoting motion between the second arm portion and the grip. A method of adjusting a position of a grip of a cyclic stick in a rotorcraft cabin is also discussed.
A method of operating an automated fiber placement machine including determining an effective length and a steering radius of a localized curved portion of a path and obtaining data including combinations of effective length and steering radius reference values each associated with a corresponding one of maximum speed values. A predetermined defect is avoided when the tape is laid along a curved path characterized by any of the combinations of effective length and steering radius reference values and laid at the corresponding maximum speed value. The method further includes determining a maximum speed based on the maximum speed values of the data in function of a correspondence between the effective length and the steering radius of the curved path and the combinations of effective length and steering radius reference values, selecting a speed for laying the tape being at most the maximum speed, and laying the tape on the surface.
An aspect provides a skid landing gear assembly including a cross member disposed between a first skid tube and a second skid tube, and a tension cable member configured to be disposed in the cross member; wherein the tension cable member resists outward deflection of at least a portion of the skid landing gear assembly when a downward load is applied to the skid landing gear assembly. In other aspects, there are methods of avoiding ground resonance in a skid landing gear assembly, methods of assembling a skid landing gear assembly, methods of operating a helicopter with a skid landing gear assembly, and methods of improving the service life of a skid landing gear assembly.
B64F 5/00 - Tracé, fabrication, assemblage, nettoyage, entretien ou réparation des aéronefs, non prévus ailleursManipulation, transport, test ou inspection de composants d’aéronefs, non prévus ailleurs
B64C 25/32 - Trains d'atterrissage caractérisés par les éléments de contact avec le sol ou une surface analogue
38.
AUTOMATIC HEADING CORRECTION FOR DIRECTIONAL GYROSCOPES
A navigation system for vehicles, such as rotorcraft, includes a directional gyroscope having a magnetic heading correction mode, a nonmagnetic manual heading correction mode and a nonmagnetic automatic heading correction mode. A magnetic field sensor is operably coupled to the directional gyroscope and is operable to generate magnetic north-based signals. A heading correction input is operably coupled to the directional gyroscope and is operable to generate manual signals upon actuation thereof. A global positioning system sensor is operably coupled to the directional gyroscope and is operable to generate track-based signals. In the magnetic heading correction mode, the directional gyroscope receives the magnetic north- based signals for heading corrections. In the nonmagnetic manual heading correction mode, the directional gyroscope receives the manual signals for heading corrections. In the nonmagnetic automatic heading correction mode, the directional gyroscope periodically receives the track-based signals for heading corrections.
An emergency escape window for a rotorcraft includes a window frame, a window pane set inside the window frame, a plurality of pins connecting the window frame to the fuselage of the rotorcraft, and a release mechanism having at least one actuator connected to a respective pin and constructed to retract the pin from the window frame. The escape window can then be pivoted away and/or completely detached from the fuselage in the event of an emergency to allow occupants to safely exit the rotorcraft. The disclosure also relate to a method of operating an emergency escape window for a rotorcraft and to a rotorcraft having an emergency escape window.
A system is provided in one example embodiment and may include a first reservoir for a lubricant; a second reservoir for the lubricant, wherein the first reservoir and the second reservoir are interconnected; a first pumping element to pump the lubricant from the first reservoir at a first flow rate; a second pumping element to pump the lubricant at a second flow rate, wherein the first flow rate and the second flow rate are different; and a gearbox coupled to the first pumping element and the second pumping element. The first reservoir may have a larger volume than the second reservoir and the first flow rate may be higher than the second flow rate.
A method for operating a sensor system includes detecting a first wake trigger by a plurality of sensors for a component disposed in a remote location, generating, by each sensor, sensor service data that includes a battery charge level of the sensor, determining an active sensor according to the sensor service data of each sensor of the plurality of sensors, and assigning the active sensor to enter an active mode assigning each sensor of the plurality of sensors, other than the active sensor, to enter a sleep mode, generating, by the active sensor, sensor reading data for the component until an inactive trigger is detected, sending the sensor reading data using a wireless transmission to a sensor data server, and leaving the active mode by the active sensor and entering a sleep mode in response to the active sensor detecting an inactive trigger.
G08B 21/00 - Alarmes réagissant à une seule condition particulière, indésirable ou anormale, et non prévues ailleurs
H04Q 9/00 - Dispositions dans les systèmes de commande à distance ou de télémétrie pour appeler sélectivement une sous-station à partir d'une station principale, sous-station dans laquelle un appareil recherché est choisi pour appliquer un signal de commande ou pour obtenir des valeurs mesurées
B64D 45/00 - Indicateurs ou dispositifs de protection d'aéronefs, non prévus ailleurs
G07C 5/00 - Enregistrement ou indication du fonctionnement de véhicules
42.
Integrated capacitive discharge electrical bonding assurance system
In one embodiment, an aircraft electronics system includes a hardware processor, a charge collection circuit to collect charge; a switching circuit controlled by the hardware processor to discharge the charge collected on the charge collection circuit through a bonding circuit formed from a chassis and a bonding surface; and a voltage measurement circuit to measure a voltage difference between measurement terminals across the chassis and the bonding surface.
G01R 27/26 - Mesure de l'inductance ou de la capacitanceMesure du facteur de qualité, p. ex. en utilisant la méthode par résonanceMesure de facteur de pertesMesure des constantes diélectriques
H02J 7/00 - Circuits pour la charge ou la dépolarisation des batteries ou pour alimenter des charges par des batteries
G01R 31/02 - Essai des appareils, des lignes ou des composants électriques pour y déceler la présence de courts-circuits, de discontinuités, de fuites ou de connexions incorrectes de lignes
B64D 45/02 - Dispositifs de protection contre la foudreDéperditeurs de potentiel
H02H 5/10 - Circuits de protection de sécurité pour déconnexion automatique due directement à un changement indésirable des conditions non électriques normales de travail avec ou sans reconnexion sensibles à une détérioration mécanique, p. ex. rupture de ligne, rupture de connexion de terre
B64D 43/00 - Aménagements ou adaptations des instruments
G01R 31/00 - Dispositions pour tester les propriétés électriquesDispositions pour la localisation des pannes électriquesDispositions pour tests électriques caractérisées par ce qui est testé, non prévues ailleurs
H02J 7/34 - Fonctionnement en parallèle, dans des réseaux, de batteries avec d'autres sources à courant continu, p. ex. batterie tampon
H02H 1/00 - Détails de circuits de protection de sécurité
H02H 3/04 - Circuits de protection de sécurité pour déconnexion automatique due directement à un changement indésirable des conditions électriques normales de travail avec ou sans reconnexion Détails avec signalisation ou supervision additionnée à la déconnexion, p. ex. pour indiquer que l'appareil de protection a fonctionné
H05F 1/00 - Prévention de la formation des charges électrostatiques
In one embodiment, a split torque gearbox can include a first compound gear and a second compound gear. The compound gears can each include a piston housing with a fluid inlet and a piston received in the piston housing and defining a space within the first piston housing exposed to the fluid inlet. The split torque gearbox can include a fluid line coupled to each of the fluid inlets to supply a fluid to the pistons at a predetermined pressure, the fluid line coupled to the second fluid inlet to supply fluid to the second piston assembly at the predetermined pressure. Pressure developed in the pistons is equal for all gear shafts, and can equalize torque imbalances in the split torque gearbox.
F16H 57/022 - Ajustement d'arbres ou de paliers de transmission
F16H 1/22 - Transmissions à engrenages pour transmettre un mouvement rotatif sans engrenages à mouvement orbital comportant plus de deux organes engrenés avec plusieurs arbres d’entraînement ou entraînésTransmissions à engrenages pour transmettre un mouvement rotatif sans engrenages à mouvement orbital comportant plus de deux organes engrenés avec dispositions pour répartir le couple entre plusieurs arbres intermédiaires
In one embodiment, a centrifugal force generating device comprises a first hydraulic rotor, a second hydraulic rotor, and one or more hydraulic control valves. The first hydraulic rotor comprises a first mass and is configured to rotationally drive the first mass around a first axis of rotation using a first flow of hydraulic fluid through the first hydraulic rotor. The second hydraulic rotor comprises a second mass and is configured to rotationally drive the second mass around a second axis of rotation using a second flow of hydraulic fluid through the second hydraulic rotor. The one or more hydraulic control valves are configured to control the first flow of hydraulic fluid through the first hydraulic rotor and the second flow of hydraulic fluid through the second hydraulic rotor.
B06B 1/18 - Procédés ou appareils pour produire des vibrations mécaniques de fréquence infrasonore, sonore ou ultrasonore dans lesquels le vibrateur est déclenché par pression de fluide
F16F 15/023 - Suppression des vibrations dans les systèmes non rotatifs, p. ex. dans des systèmes alternatifsSuppression des vibrations dans les systèmes rotatifs par l'utilisation d'organes ne se déplaçant pas avec le système rotatif utilisant des moyens fluides
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]
According to one embodiment, a rotorcraft includes a body, a rotor blade, a drive system that can be operated to rotate the rotor blade, and an emergency valve control unit. The drive system contains a first gearbox assembly, a second gearbox assembly, a first lubrication system that can deliver lubricant to the first gearbox assembly, and a second lubrication system that can deliver lubricant to the second gearbox assembly. The drive system also contains an emergency valve that can be opened to deliver lubricant from the first lubrication system to the second gearbox assembly. The emergency valve control unit can instruct the emergency valve to open.
A cable reel restraint device comprises a cable reel, a retractable cable, first and second springs, first and second attachment interfaces, and a preload selection control. The retractable cable is configured to extend from and retract onto the cable reel. The first spring is configured to exert force for preloading the second spring, and the second spring is configured to exert force for retracting the retractable cable. The first attachment interface is coupled to the cable reel by a first spherical bearing, and the second attachment interface is coupled to the retractable cable by a second spherical bearing. Moreover, the first and second attachment interfaces are configured for being fastened to first and second attachment points. The preload selection control is configured to select a particular preload magnitude and cause the first spring to preload the second spring with a load of the particular preload magnitude.
A mounting assembly for coupling an accessory to a frame including a base configured to be coupled to the frame; the base having a hollow portion; the hollow portion including a receiving end including a tapered socket; an internal interlocking portion adjacent to the tapered socket; and a securing end opposite from the receiving end; a shaft configured to be connected to an accessory at a first end and received in the hollow portion of the base in an engaged position, the shaft including a tapered boss adjacent to the first end, the tapered boss configured to engage the tapered socket; an external interlocking portion adjacent to the tapered boss configured to engage the internal interlocking portion; and a second end opposite from the first end, the second end including a threaded surface; wherein when the shaft is in an engaged position, the shaft is static in the hollow portion.
B64D 29/06 - Fixation des nacelles, carénages ou capotages
F16B 21/12 - Dispositifs sans filetage pour empêcher le mouvement relatif selon l'axe d'une broche, d'un ergot, d'un arbre ou d'une pièce analogue par rapport à l'organe qui l'entoureFixations à ergots et douilles largables sans filetage à parties séparées par goupilles d'arrêt ou goupilles fendues enfoncées dans des trous
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]
49.
Multirotor aircraft with collective for autorotation
A multirotor aircraft comprises at least three proprotors. Each proprotor has a plurality of rotor blades pivotably attached to a mast assembly. When a rotor blade pitch angle is changed for a proprotor, all rotor blades on the proprotor change to a same pitch angle. The proprotors are configured to spin freely when a power source is disengaged or fails. In various embodiments, one or more engines provides power to each proprotor, or at least one engine provides power to two or more proprotors. A rotor blade control system is configured to control a collective rotor blade pitch angle on each proprotor independently of the rotor blade pitch on the other proprotors. The rotor blade control system is configured to set a negative collective rotor blade pitch angle on an unpowered proprotor, such as in response to manual inputs by a pilot or in response to current engine conditions.
B64C 11/30 - Mécanismes de changement de pas des pales
B64D 45/00 - Indicateurs ou dispositifs de protection d'aéronefs, non prévus ailleurs
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 27/28 - Giravions complexes, c.-à-d. aéronefs utilisant en vol à la fois les caractéristiques de l'avion et celles du giravion avec hélices propulsives de déplacement pouvant pivoter pour agir comme rotors de sustentation
B64C 29/00 - Aéronefs capables d'atterrir ou de décoller à la verticale, p. ex. aéronefs à décollage et atterrissage verticaux [ADAV, en anglais VTOL]
In one embodiment, a tiltrotor aircraft may comprise a fuselage; a biplane wing coupled to the fuselage, wherein the biplane wing comprises an upper wing structure and a lower wing structure; a plurality of tiltrotors coupled to the biplane wing; and at least one engine to power the plurality of tiltrotors.
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 3/38 - Réglage des ailes complètes ou de certaines parties de ces ailes
B64C 9/14 - Surfaces ou éléments de commande réglables, p. ex. gouvernes de direction formant des fentes
B64C 39/08 - Aéronefs non prévus ailleurs à ailes multiples
B64C 15/12 - Commande de l'assiette, de la direction du vol ou de l'altitude par jets réactifs les jets étant des jets propulsifs le groupe propulseur étant basculable
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
There is provided a rotorcraft, including a body, including a front portion and a tail portion; a main rotor system coupled to the front portion of the body, the main rotor system operable to provide a lifting force on the body; and an anti-torque system coupled to the tail portion of the body, the anti-torque system including a primary tail rotor system and a secondary tail rotor system; wherein the primary tail rotor system and the secondary tail rotor system are operable to provide a first anti-torque force and a second anti-torque force. In other aspects, there are methods of providing anti-torque force in a rotorcraft.
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
A rotor system including a hub; a rim configured to rotate about the hub, the rim including an interior surface and an engagement surface; a plurality of rotor blades extending from the hub and coupled to the interior surface of the rim; and one or more outer drive gears disposed adjacent to the engagement surface of the rim; each of the one or more outer drive gears including a plurality of teeth for engaging the engagement surface of the rim; wherein the one or more outer drive gears are configured to rotate the rim such that the plurality of rotor blades rotates about the hub. Other aspects provide an aircraft rotor system and methods of operating an aircraft rotor system.
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
An intentionally activated frangible bonding system comprises a frangible adhesive, adhesive primer, composite material matrix, and/or the like, having a polydispersion of at least one additive spread throughout the frangible bonding material. The additive degrades a bond provided by the frangible bonding material, upon application of a specific energy to the frangible bonding material. An energy emitter is configured to selectively direct the specific energy toward a structure or assembly comprising components bonded by the frangible bonding material to degrade the frangible bonding material bonding the components for disassembly.
B32B 43/00 - Opérations spécialement adaptées aux produits stratifiés et non prévues ailleurs, p. ex. réparationAppareils pour ces opérations
B32B 38/00 - Opérations auxiliaires liées aux procédés de stratification
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
Systems and methods of operating a test apparatus to simulate testing a production aircraft component include assembling a test assembly having a test specimen and a wear protection material disposed on opposing sides of the test specimen, an outer plate disposed on each side of the test specimen in contact with the wear protection material, and a bolt disposed through the test specimen and the outer plates and applying a preload against the wear protection material. The test assembly is secured in a test machine, and the test machine is operated to provide a predetermined displacement of the test specimen relative to the outer plates at a predetermined frequency at a determined frequency of displacement cycles. The preload, the predetermined displacement, and the predetermined frequency of displacement cycles are determined through finite element analysis of an analytical model of the production component.
G01N 3/00 - Recherche des propriétés mécaniques des matériaux solides par application d'une contrainte mécanique
G01N 3/08 - Recherche des propriétés mécaniques des matériaux solides par application d'une contrainte mécanique par application d'efforts permanents de traction ou de compression
G01N 1/00 - ÉchantillonnagePréparation des éprouvettes pour la recherche
G01N 1/08 - Dispositifs pour prélever des échantillons à l'état solide, p. ex. par coupe à l'outil impliquant un outil d'extraction, p. ex. mèche cylindrique creuse ou trépan
A hybrid power system for a vertical takeoff and landing (“VTOL”) aircraft including a first power source operable to provide a power output for at least a forward flight mode; and a second power source configured to provide a high specific power output for an altitude adjustment flight mode, the second power source including an auxiliary gas generator coupled to a turbine and a drive system. In other aspects, there is provided a VTOL aircraft and methods for providing power to a VTOL aircraft.
B64D 27/10 - Aéronefs caractérisés par le type ou la position des groupes moteurs du type à turbine à gaz
B64D 27/24 - Aéronefs caractérisés par le type ou la position des groupes moteurs utilisant la vapeur ou l'énergie de ressorts
B64D 41/00 - Installations génératrices de puissance pour servitudes auxiliaires
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]
F02C 6/14 - Ensembles fonctionnels de turbines à gaz comportant des moyens pour emmagasiner l'énergie, p. ex. pour faire face à des pointes de charge
B64C 27/28 - Giravions complexes, c.-à-d. aéronefs utilisant en vol à la fois les caractéristiques de l'avion et celles du giravion avec hélices propulsives de déplacement pouvant pivoter pour agir comme rotors de sustentation
B64D 37/30 - Circuits de carburant pour carburants particuliers
B64D 27/02 - Aéronefs caractérisés par le type ou la position des groupes moteurs
56.
Exhaust manifold for combining system exhaust plume
Disclosed herein is an aircraft that includes an exhaust manifold for combining one or more system exhaust paths located upstream of equipment inlets and directing the exhausts upwards towards the rotor linkages such that the exhaust is expelled and diffused forward of the equipment inlets. According to one aspect of the present disclosure, the exhaust manifold includes a structure for supporting a transmission cowling at the top of the aircraft and/or on the sides of the aircraft. For example, the exhaust manifold may include a platform that contains the exhaust ducts and may include a frame extending from the platform that follows the contours of the cowling, such that the cowling lays along the support frame for additional mechanical support.
F01N 13/10 - Autres aménagements ou adaptations des tubulures d'échappement des collecteurs d'échappement
B64C 27/00 - GiravionsRotors propres aux giravions
B64D 33/08 - Aménagement sur les aéronefs des éléments ou des auxiliaires des ensembles fonctionnels de propulsion, non prévu ailleurs des systèmes de refroidissement des ensembles fonctionnels de propulsion
F01P 1/06 - Disposition du refroidissement d'autres parties des moteurs ou "machines"
F01P 11/10 - Guidage ou conduite de l'air de refroidissement vers ou depuis les échangeurs de chaleur "liquide vers air"
In an embodiment, a rotorcraft includes: tail rotor blades; a tail rotor actuator coupled to the tail rotor blades such that the pitch of the tail rotor blades varies according to a current extension of the tail rotor actuator; pilot flight controls electrically coupled to the tail rotor actuator; and a flight control computer electrically coupled to the tail rotor actuator and the pilot flight controls, the flight control computer configured to: determine the current extension of the tail rotor actuator; determine whether the current extension of the tail rotor actuator is within a margin of a maximum extension of the tail rotor actuator; and indicate a first warning to a pilot in response to the current extension of the tail rotor actuator being within the margin of the maximum extension of the tail rotor actuator.
B64D 45/00 - Indicateurs ou dispositifs de protection d'aéronefs, non prévus ailleurs
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
B64D 43/00 - Aménagements ou adaptations des instruments
B64C 13/04 - Dispositifs amorçant la mise en œuvre actionnés par l'homme
B64C 13/50 - Dispositifs de transmission avec amplification de puissance utilisant l'énergie électrique
There is provided an ice protection system for a rotary aircraft, including a rotor blade susceptible to an ice buildup having an inboard portion and an outboard portion, the length of the inboard portion and the length of the outboard portion define a total length of the rotor blade; a first deicing system coupled to the inboard portion of the rotor blade, the first deicing system including a plurality of spanwise zones; and a second deicing system coupled to the outboard portion of the rotor blade, the second deicing system including a plurality of chordwise zones. In one aspect, there is provided a deicing system for a rotary aircraft. In another aspect, there is a method to de-ice a rotor blade of an aircraft.
In one embodiment of the present disclosure, there is provided an aircraft having a bi-folding cowl for providing full access to equipment without completely removing the cowl. The bi-folding cowl has an upper portion and a lower portion mechanically connected along the adjacent edges, where the upper and lower portions fold so that the inner surfaces face each other when opened. In another embodiment, the bi-folding cowl has at least three maintenance positions, including partially-opened, fully-opened, and fully-opened, lying flat on the surface of the aircraft.
In one embodiment of the present disclosure, there is provided an aircraft that includes a cowling having a j-track mounted on the inwardly facing surface and a rod pivotally connected to a stationary part of the aircraft at a first end and moveable within the j-track at a second end, so that, when the cowling is opened, the second end moves to lock into the j-shaped portion and hold the cowling open. In various embodiments, the first end may be pivotally connected to the aircraft by a quick release pin, and the second end may be connected to the j-track by a torsion spring. In another embodiment of the present disclosure, the cowling is a bi-folding cowl having an upper portion and a lower portion, where the rod and the lower portion may include structures for retaining the lower portion in an opened position.
This disclosure relates to an air inlet for an aircraft with an integrated hand hold. One innovative aspect of the subject matter described herein can be implemented as an air inlet on the exterior surface of a cowling for a rotorcraft, wherein the air inlet having a scoop that includes a bottom surface having a wide, flat, front edge that angles downward towards the back, an opening in the back for air to enter, and two lateral sides coupled to the bottom surface, where the two sides are planar on a top surface and become longer in height towards the opening in the back, and hand hold, where the hand hold is a trough or an indentation in the bottom surface of the scoop that extends along a side.
B64D 33/02 - Aménagement sur les aéronefs des éléments ou des auxiliaires des ensembles fonctionnels de propulsion, non prévu ailleurs des entrées d'air de combustion
B64C 1/14 - FenêtresPortesTrappes d'évacuation ou panneaux de visiteStructures de cadres environnantsVerrièresPare-brise
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 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
In one embodiment, a rotor hub comprises a hub plate, a yoke for attaching a plurality of rotor blades, a plurality of yoke support bearings, and a plurality of cushioned damper bearings for attaching a plurality of dampers.
An enclosure including a bottom side having a pass through opening, a connector surface having one or more connector openings, a first side adjacent to the connector surface, and a second side having at least a portion of an access opening, where the first side, the second side, the connector surface and the bottom side bound an interior cavity. The enclosure further includes one or more connectors, each of the one or more connectors disposed in a respective connector opening of the one or more connector openings and extending from the interior cavity, through the connector surface, and a cover attached to an exterior surface of at least the second side, the cover covering the access opening.
B60R 16/023 - Circuits électriques ou circuits de fluides spécialement adaptés aux véhicules et non prévus ailleursAgencement des éléments des circuits électriques ou des circuits de fluides spécialement adapté aux véhicules et non prévu ailleurs électriques pour la transmission de signaux entre des parties ou des sous-systèmes du véhicule
B60R 16/08 - Circuits électriques ou circuits de fluides spécialement adaptés aux véhicules et non prévus ailleursAgencement des éléments des circuits électriques ou des circuits de fluides spécialement adapté aux véhicules et non prévu ailleurs de fluides
B64C 13/50 - Dispositifs de transmission avec amplification de puissance utilisant l'énergie électrique
A method for repairing damage to a composite part includes creating an aperture through the composite part and preparing the surfaces surrounding the aperture on both sides of the part; inserting a plurality of resin impregnated fibers through the aperture and spreading the end portions of the plurality of fibers radially against the prepared surfaces on both sides of the part; and maintaining contact of the plurality of fibers with the prepared surfaces while the resin cures.
B29C 73/06 - Réparation d'articles faits de matières plastiques ou de substances à l'état plastique, p. ex. d'objets façonnés ou fabriqués par utilisation de techniques couvertes par la présente sous-classe ou la sous-classe utilisant des éléments préformés utilisant des bouchons insérés dans la perforation et l'obturant
B29C 70/30 - 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
D03D 1/00 - Tissus conçus pour faire des articles particuliers
D03D 15/00 - Tissus caractérisés par la matière, la structure ou les propriétés des fibres, des filaments, des filés, des fils ou des autres éléments utilisés en chaîne ou en trame
B29C 70/08 - 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 comprenant des combinaisons de différentes formes de renforcements fibreux incorporés dans une matrice, formant une ou plusieurs couches, avec ou sans couches non renforcées
B29L 31/30 - Véhicules, p. ex. bateaux ou avions, ou éléments de leur carrosserie
B32B 17/10 - Produits stratifiés composés essentiellement d'une feuille de verre ou de fibres de verre, de scorie ou d'une substance similaire comprenant du verre comme seul composant ou comme composant principal d'une couche adjacente à une autre couche d'une substance spécifique de résine synthétique
66.
Adaptable rotor control system for a variable number of blades
In one embodiment, a rotor hub comprises a yoke for attaching a plurality of rotor blades, a constant velocity joint to drive torque from a mast to the yoke and to enable the yoke to pivot, and a rotor control system configured to adjust an orientation of the plurality of rotor blades. Moreover, the rotor control system comprises: a swashplate, a phase adapter fulcrum, a plurality of actuators controlled based on a flight control input, a plurality of lower pitch links configured to transfer motion between the plurality of actuators and the swashplate, a plurality of phase adjustment levers configured to adjust a control phase associated with motion transferred between the plurality of actuators and the plurality of lower pitch links, and a plurality of upper pitch links configured to adjust a pitch of the plurality of rotor blades, wherein there are more upper pitch links than lower pitch links.
B64C 11/06 - Montage des pales dans le cas de pales à pas variable
B64C 11/32 - Mécanismes de changement de pas des pales mécaniques
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 11/30 - Mécanismes de changement de pas des pales
B64C 27/605 - Transmissions, p. ex. en liaison avec les moyens déclenchant ou agissant sur les pales mécaniques comportant un plateau oscillant, des mécanismes à tringlerie ou à came
An aircraft rotor assembly has a central yoke and a plurality of rotor blades coupled to the yoke for rotation with the yoke about an axis, each blade having a Lock number of approximately 5 or greater. A lead-lag pivot for each blade is a radial distance from the axis and allows for in-plane lead-lag motion of the associated blade relative to the yoke, each pivot allowing for in-plane motion from a neutral position of at least 1 degree in each of the lead and lag directions. Lead and lag motion of each blade is opposed by a biasing force that biases the associated blade toward the neutral position, and the biasing force is selected to achieve a first in-plane frequency of greater than 1/rev for each blade.
In one embodiment, a rotor hub comprises a hub body, and a plurality of blade grips configured for attaching a plurality of rotor blades. The rotor hub further comprises a plurality of centrifugal force bearings coupled to the plurality of blade grips, wherein a focus of the plurality of centrifugal force bearings is aligned with a centerline of a rotor mast. The rotor hub further comprises a plurality of drive links configured to transfer torque to the plurality of rotor blades, wherein the plurality of drive links is positioned to correspond with a leading edge side of the plurality of rotor blades. The rotor hub further comprises a plurality of pitch horns configured to adjust a pitch of the plurality of rotor blades.
B64C 27/59 - Transmissions, p. ex. en liaison avec les moyens déclenchant ou agissant sur les pales mécaniques
B64C 27/78 - Mécanismes pour la commande du réglage ou du mouvement de la pale par rapport à la tête du rotor, p. ex. mouvement de traînée en conjonction avec le réglage du pas des pales du rotor anticouple
69.
Adaptable rotor control system for a variable number of blades
In one embodiment, a rotor hub comprises a yoke for attaching a plurality of rotor blades, a constant velocity joint to drive torque from a mast to the yoke and to enable the yoke to pivot, and a rotor control system configured to adjust an orientation of the plurality of rotor blades. Moreover, the rotor control system comprises: a swashplate, an adapter ring, a plurality of actuators controlled based on a flight control input, a plurality of lower pitch links configured to transfer motion between the swashplate and the adapter ring, a plurality of phase adjustment levers configured to adjust a control phase associated with motion transferred between the swashplate and the adapter ring, and a plurality of upper pitch links configured to adjust a pitch of the plurality of rotor blades, wherein there are more upper pitch links than lower pitch links.
B64C 27/33 - Rotors comportant des bras qui peuvent fléchir
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 29/00 - Aéronefs capables d'atterrir ou de décoller à la verticale, p. ex. aéronefs à décollage et atterrissage verticaux [ADAV, en anglais VTOL]
70.
Cable-free and strut-free fairing for supporting a person
One example of a fairing for a rotorcraft includes a core material, an inner housing on a side of the core material, an outer housing on another side of the core material opposite the inner housing, and a hinge. The hinge is configured to move the fairing between an open position and a closed position. In the open position, the inner housing is configured to receive a foot traffic load while the outer housing is configured to transfer the foot traffic load to a fuselage of the rotorcraft. In the closed position, the inner housing is configured to stow in a compartment of the rotorcraft while the outer housing is configured to provide an outer mold line of the rotorcraft in the closed position.
An example lubrication system for a rotating component has a primary lubrication system providing continuous lubrication during normal operation of the rotating component and secondary lubrication system with a reservoir co-rotating with the component. The reservoir is continuously replenished from the primary lubrication system during normal operation of the rotating system, with the lubricant being forced through a discharge orifice by the centrifugal force generated by the rotation toward, for example, a bearing or a gear. When the primary pressurized lubrication system fails, lubrication will continue to be provided by the lubricant in the supplemental lubricant reservoir while the rotation speed or power supplied to the shaft is controllably decreased in an emergency.
F16N 7/36 - Installations à huile ou autre lubrifiant non spécifié, à réservoir ou autre source portés par la machine ou l'organe machine à lubrifier avec alimentation par pompage effectué par l'organe à lubrifier ou par un arbre de la machineLubrification centrifuge
F16H 57/04 - Caractéristiques relatives à la lubrification ou au refroidissement
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
F16C 33/66 - Pièces ou détails particuliers pour la lubrification
In one embodiment, a method may comprise coupling a plurality of reinforcement fibers to a plurality of spherical components; inserting the plurality of spherical components into an enclosure; and heating the enclosure to cause the plurality of spherical components to expand, wherein the plurality of spherical components expands to form a geodesic structure, wherein the geodesic structure comprises a plurality of polyhedron components configured in a geodesic arrangement.
B29C 73/04 - Réparation d'articles faits de matières plastiques ou de substances à l'état plastique, p. ex. d'objets façonnés ou fabriqués par utilisation de techniques couvertes par la présente sous-classe ou la sous-classe utilisant des éléments préformés
B64C 1/08 - Structures géodésiques ou autres structures treillis
B29C 44/44 - Alimentation en matière à mouler dans une cavité de moulage fermée, c.-à-d. pour la fabrication d'objets de longueur définie sous forme de particules ou de grains expansibles
B64C 3/22 - Structures géodésiques ou autres structures en treillis
B29K 63/00 - Utilisation de résines époxy comme matière de moulage
A noise control system for a ducted rotor assembly, the ducted rotor assembly including a hub, a duct, and two or more blades coupled to the hub and supported by the duct. The noise control system including a microphone configured to receive a sound input generated by the ducted rotor assembly, the microphone configured for association with the hub; a speaker unit configured to generate a cancellation noise, the speaker configured for association with the hub; and a controller operably connected to the microphone and the speaker unit, the controller configured to selectively adjust harmonics of the cancellation noise to reduce an acoustic signature of the ducted rotor assembly. In another aspect, there is provided a rotorcraft with a ducted rotor assembly in a tail portion including a noise control system. In a third aspect, there is a method of reducing an acoustic signature of a ducted rotor assembly.
G10K 11/178 - Procédés ou dispositifs de protection contre le bruit ou les autres ondes acoustiques ou pour amortir ceux-ci, en général utilisant des effets d'interférenceMasquage du son par régénération électro-acoustique en opposition de phase des ondes acoustiques originales
G10K 11/175 - Procédés ou dispositifs de protection contre le bruit ou les autres ondes acoustiques ou pour amortir ceux-ci, en général utilisant des effets d'interférenceMasquage du son
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
H04R 1/28 - Supports de transducteurs ou enceintes conçus pour réponse de fréquence spécifiqueEnceintes de transducteurs modifiées au moyen d'impédances mécaniques ou acoustiques, p. ex. résonateur, moyen d'amortissement
In a first aspect, there is a helicopter skid landing gear assembly including a front cross tube configured to interconnect two skid tubes; and a rear cross tube configured to interconnect two skid tubes; wherein at least one of the cross tubes comprises a monolithic metallic tube having a cross-section with a round exterior shape and an elliptical hollow portion therein. In a second aspect, there is a method for retrofitting a helicopter with a landing gear assembly; the method including providing a front cross tube and a rear cross tube, at least one of the front cross tube and the rear cross tube comprises a monolithic metallic tube having a cross-section with a substantially round exterior shape and an elliptical hollow portion therein; and connecting the front cross tube and rear cross tube to a fuselage.
The present invention achieves technical advantages as an engine compartment drainage system that allows fluid on an engine deck to exit an engine compartment, while shielding fluid from airflow. A fluid drainage apparatus utilizes a funnel member to direct fluid to an external drain line. A drain shield circumscribes the top end of the funnel member and upwardly extending therefrom and directs airflow away from the funnel member. A plurality of deck holes are disposed in the drain shield, such that fluid on the deck can enter the funnel member and exit the engine compartment. A fluid drainage system, disposes the fluid drainage apparatus in an engine deck to allow fluid on the deck to enter a funnel member of the apparatus and direct it toward the external drain line.
F02B 77/10 - Dispositifs de sécurité relatifs aux explosions dans le carter
A62C 3/08 - Prévention, limitation ou extinction des incendies spécialement adaptées pour des objets ou des endroits particuliers dans les véhicules, p. ex. les véhicules routiers dans les avions
F02B 77/04 - Nettoyage, prévention de la corrosion, de l'érosion ou des dépôts indésirables dans les moteurs à combustion
F01P 1/06 - Disposition du refroidissement d'autres parties des moteurs ou "machines"
F01P 11/12 - Filtrage, refroidissement ou silencieux pour l'air de refroidissement
F16N 31/00 - Dispositifs pour recueillir ou retenir le lubrifiant dans les machines ou appareils ou pour l'en évacuer
One example of a fairing for a rotorcraft includes an outer mold line portion (OML portion) and a bearing portion extending from the OML portion. The OML portion provides at least a portion of an outer mold line of the rotorcraft. Both the OML portion and the bearing portion shield a portion of a structural member. The bearing portion can protect the portion of the structural member from damage resulting from foot traffic associated with accessing an area nearby the structural member.
A method for facilitating the design and manufacturing of a tiltrotor aircraft, including the steps of: determining a compatible mission data set; identifying lift propulsion module components for the compatible mission data set; determining compatible specifications; and generating a design for a lift propulsion module; wherein the lift propulsion module is configured to be connected to at least two different fuselages. There is also a method of designing a tiltrotor aircraft, comprising the step of modularizing a lift propulsion system, wherein the lift propulsion system is configured to be connected to at least two different fuselages. In another aspect, there is a tiltrotor aircraft including a fuselage; and a lift propulsion module, the lift propulsion module including a mounting surface; wherein the lift propulsion module is coupled to the fuselage on the mounting surface. Also included are methods of assembling and systems including a lift propulsion module.
G06F 30/15 - Conception de véhicules, d’aéronefs ou d’embarcations
B64F 5/10 - Fabrication ou assemblage d’aéronefs, p. ex. gabarits à cet effet
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]
B64F 5/00 - Tracé, fabrication, assemblage, nettoyage, entretien ou réparation des aéronefs, non prévus ailleursManipulation, transport, test ou inspection de composants d’aéronefs, non prévus ailleurs
B64C 1/00 - FuselagesCaractéristiques structurales communes aux fuselages, voilures, surfaces stabilisatrices ou organes apparentés
78.
Methods of customizing, manufacturing, and repairing a rotor blade using additive manufacturing processes
In a first aspect, there is a method of making a rotor blade, including designing at least one of an upper skin, a lower skin, a support network, and components therefor; and forming at least one of the upper skin, the lower skin, a support network, and components therefor using an additive manufacturing process. In a second aspect, there is an airfoil member having a root end, a tip end, a leading edge, and a trailing edge, the airfoil member including an upper skin; a lower skin; and a support network having a plurality of interconnected support members in a lattice arrangement and/or a reticulated arrangement, the support network being configured to provide tailored characteristics of the airfoil member. Also provided are methods and systems for repairing an airfoil member.
B22F 5/04 - Fabrication de pièces ou d'objets à partir de poudres métalliques caractérisée par la forme particulière du produit à réaliser d'aubes de turbines
B22F 7/06 - Fabrication de couches composites, de pièces ou d'objets à base de poudres métalliques, par frittage avec ou sans compactage de pièces ou objets composés de parties différentes, p. ex. pour former des outils à embouts rapportés
B33Y 50/00 - Acquisition ou traitement de données pour la fabrication additive
B22F 3/105 - Frittage seul en utilisant un courant électrique, un rayonnement laser ou un plasma
B22F 3/00 - Fabrication de pièces ou d'objets à partir de poudres métalliques, caractérisée par le mode de compactage ou de frittageAppareils spécialement adaptés à cet effet
B23P 6/00 - Remise en état ou réparation des objets
B23K 15/00 - Soudage ou découpage par faisceau d'électrons
B29C 73/04 - Réparation d'articles faits de matières plastiques ou de substances à l'état plastique, p. ex. d'objets façonnés ou fabriqués par utilisation de techniques couvertes par la présente sous-classe ou la sous-classe utilisant des éléments préformés
F01D 5/00 - AubesOrganes de support des aubesDispositifs de chauffage, de protection contre l'échauffement, de refroidissement, ou dispositifs contre les vibrations, portés par les aubes ou les organes de support
B29L 31/08 - Pales pour rotors, stators, ventilateurs, turbines ou dispositifs analogues, p. ex. hélices
A an open relay device and system includes a chassis having one or more openings; external connectors on a first wall of the chassis, the external connectors having a plurality of external connection terminals; ground bussing modules attached to a second wall of the chassis; junction bussing modules attached to a third wall of the chassis; relay sockets attached to a fourth wall of the chassis; and wiring electrically connecting the external connectors to the ground bussing modules, the junction bussing modules, and the relay sockets, the wiring further electrically connecting the relay sockets to the junction bussing modules and the ground bussing modules.
H02B 1/04 - Montage sur ces dispositifs d'interrupteurs ou d'autres dispositifs en général, l'interrupteur ou le dispositif étant muni ou non d'une enveloppe
B64D 43/00 - Aménagements ou adaptations des instruments
A system and method for measuring, or otherwise determining pitch length adjustments to a pitch link coupled to a rotor blade in a rotorcraft includes vertical track adjustment indicators machined onto an exterior of the tube of the pitch link and a vertical reference indicator machined onto an exterior of the upper or the lower rod of the pitch link. A metric of a pitch length adjustment can be determined by tracking or counting how many track adjustment indicators pass the reference indicator while the tube of the pitch link is being turned in either direction for increasing or decreasing the pitch length. The track adjustment indicators can be relied upon to track one or a series of adjustments for tracking a rotor blade installed in a rotor assembly.
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 27/605 - 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 method of optimizing a planetary gear system for continued operation after failure of a planet gear includes providing a planetary gear system and reducing a backup ratio of a planet gear of the planetary gear system by reducing a rim thickness of the planet gear.
A method of avoiding gear tooth interference in a planetary gear system includes designing and building a planetary gear system comprising a selected base pitch and tooth length for planet gears, breaking a rim of one of the planet gears, and verifying whether tooth tip interference occurs during operation of the planetary gear system.
A system and method for providing state comparison of redundant processors used, e.g. to control a rotor craft. A primary microprocessor is configured to receive input data from a position sensor and a flight condition sensor and determine therefrom a first desired control law state, and a secondary microprocessor is configured to receive input data from the position sensor and the flight condition sensor and determine therefrom a second desired control law state. The first desired control law state from the primary microprocessor and the second desired control law state from the secondary microprocessor are compared, and (a) the first desired control law state is entered when the first desired control law state and the second desired control law state match, and (b) a last known control law state is maintained when the first desired control law state and the second desired control law state do not match.
B64C 13/50 - Dispositifs de transmission avec amplification de puissance utilisant l'énergie électrique
G05D 1/10 - Commande de la position ou du cap dans les trois dimensions simultanément
G05D 1/00 - Commande de la position, du cap, de l'altitude ou de l'attitude des véhicules terrestres, aquatiques, aériens ou spatiaux, p. ex. utilisant des pilotes automatiques
A pitch horn assembly for an aircraft including a blade attachment member having a first end, a second end configured to be coupled to a rotor blade; and a blade attachment axis extending between the first end and the second end of the blade attachment member; a moveable arm configured to be coupled to the blade attachment member at a pitch horn axis, the moveable arm having a first end configured to be coupled to a pitch link; a second end; and a moveable arm axis extending between the first end and the second end of the moveable arm; an extendable member configured to be coupled to the blade attachment member and the moveable arm of the pitch horn, wherein the extendable member moves the moveable arm about the pitch horn axis. An embodiment provides a method of adjusting a pitch-flap coupling in an aircraft.
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 rotor speed indication system configured to communicate a rotor speed operating range for a twin engine rotorcraft having a rotor during one engine inoperable conditions. The rotor speed indication system includes a governing reference indicator located on a display and configured to communicate an upper operating range threshold. A droop reference indicator located on the display and configured to communicate a lower operating range threshold. A sensor configured to measure a current rotor speed of the rotor. A dynamic rotor speed indicator located on the display and configured to communicate the current rotor speed of the rotor such that when the dynamic rotor speed indicator is positioned between the governing reference indicator and the droop reference indicator on the display, the current rotor speed of the rotor is within the rotor speed operating range.
A method for defining a threshold stress curve utilized in fatigue and/or damage tolerance analysis, the method including conducting a direct test method on a plurality of specimens with a notch to generate raw data, the notch in each of the specimens having a notch dimension; determining a plurality of analyzed data points based upon the raw data; determining a regression line based upon the plurality of data points, the regression line including an exponential portion and a power law portion; and connecting the exponential portion and the power law portion of the regression line to form a threshold stress curve based on the regression line.
G01N 3/32 - Recherche des propriétés mécaniques des matériaux solides par application d'une contrainte mécanique en appliquant des efforts répétés ou pulsatoires
G01N 3/06 - Adaptations particulières des moyens d'indication ou d'enregistrement
87.
Active vibration control system with non-concentric revolving masses
A vibration control system for a rotor hub provides vibration attenuation in an aircraft by reducing the magnitude of rotor induced vibratory. The system can include a force generating device attached to a rotor hub which rotates along with the rotor at the rotational speed of the rotor. Vibratory shear force is generated by rotating unbalanced weights each about an axis non-concentric with the rotor hub axis at high speed to create large centrifugal forces. The rotational speed of the weights can be a multiple of the rotor rotational speed to create shear forces for canceling rotor induced vibrations. The amplitude of the generated shear force is controlled by indexing the positions of the unbalanced weights relative to each other, while the phase of the shear force is adjusted by equally phasing each weight relative to the rotor.
In a first aspect, there is a method for improving a lift to drag ratio of a rotor blade, including providing a blade member having a leading edge and a trailing edge; providing a leading edge extension member; and coupling the leading edge extension member to a portion of the leading edge of the blade member to form the rotor blade. In a second aspect, there is a rotor blade including a blade member having a leading edge, and a trailing edge; and a leading edge extension member disposed on the leading edge of the blade member, wherein the leading edge extension member is configured to extend the chord length of at least a portion of the rotor blade. In a third aspect, there is a leading edge extension member for a rotor blade including a convex exterior surface configured to extend at least a portion of the chord length of the rotor blade.
In a first aspect, there is a personal air vehicle including a body having a forward portion, a central portion and an aft portion; a first ducted fan supported by the forward portion of the body; a second ducted fan supported by the aft portion of the body; and third and fourth ducted fans supported by the left and right sides of the body and pivotable relative to the body. An aspect provides a method of flying the personal air vehicle.
The present invention includes a rotorcraft drive system, method, and aircraft comprising a fixed engine; a rotating spindle that rotates a proprotor gearbox and rotor pylon between a hover and forward flight position, wherein the rotating spindle rotates about a rotation bearings on two inboard ribs of a wing member; and an interconnect drive shaft connected to the fixed engine, wherein the interconnect drive shaft passes through an aft cove of the wing member and connects to the engine via a forward-aft drive shaft, wherein the forward-aft drive shaft is connected to the proprotor gearbox to provide power to a proprotor.
B64D 35/02 - Transmission de la puissance des groupes moteurs aux hélices ou aux rotorsAménagements des transmissions spécialement adaptés à des groupes moteurs spécifiques
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]
In one embodiment, an apparatus comprises a shaft, a rotor, and a cam surface. The shaft comprises a spiral spline along a length of the shaft. The rotor comprises a blade extending from the rotor and a tubular hole extending into the rotor. The tubular hole comprises a spiral groove configured to mate with the spiral spline on the shaft. Relative rotation between the spiral spline and the spiral groove causes the rotor to linearly move along the shaft. The cam surface comprising a recession. The blade nesting in the recession to constrains rotation of the rotor about the shaft and allows linear movement of the rotor along the shaft.
B64C 27/30 - Giravions complexes, c.-à-d. aéronefs utilisant en vol à la fois les caractéristiques de l'avion et celles du giravion avec moyens permettant de réduire la traînée du rotor en période de non fonctionnement
B64C 27/26 - Giravions complexes, c.-à-d. aéronefs utilisant en vol à la fois les caractéristiques de l'avion et celles du giravion caractérisé par le fait qu'il est doté d'ailes fixes
B64C 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
One example of a cowling assembly for a rotorcraft includes a stationary fairing affixed to an airframe of the rotorcraft, an articulated fairing hinged on the stationary fairing for articulation relative to the stationary fairing between a closed position, a first partially open maintenance position and a second fully open maintenance position. The articulated fairing is supported in the first maintenance position by a for example gas-charged strut and is releasably locked in the second maintenance position against the stationary fairing by a locking mechanism. The locking mechanism includes a latch blade disposed on the stationary fairing and a latch arranged on the articulated fairing, wherein a latch pin engages with a hole or recess in the latch blade when the latch blade extends through a slot in the articulated fairing.
E05C 17/12 - Dispositifs pour tenir les battants dans une position d'ouvertureDispositifs pour limiter l'ouverture des battants ou pour tenir les battants dans une position d'ouverture par une pièce mobile disposée entre le battant et le dormantDispositifs de freinage, butées ou tampons combinés avec ces dispositifs par des moyens mécaniques par une barre mobile ou une pièce équivalente disposée entre le dormant et le battant consistant en une tringle unique
In one embodiment, there is described an inlet plenum assembly for a rotary aircraft, including: an inlet plenum defined on a first side by an inlet plenum wall and on a second side by a forward firewall assembly; the inlet plenum wall having a mechanical interface for receiving a reduction gearbox (RGB) to provide reduction gearing to the drive shaft; and the forward firewall assembly having an inlet aperture configured to receive a drive shaft to rotatably couple to an engine; wherein the forward firewall assembly includes a forward firewall upper and a forward firewall lower, the forward firewall upper configured to removably seat to the forward firewall lower.
B64D 33/02 - Aménagement sur les aéronefs des éléments ou des auxiliaires des ensembles fonctionnels de propulsion, non prévu ailleurs des entrées d'air de combustion
An apparatus includes a shaft comprising a spiral spline along a length of the shaft. A rotor comprising a blade extending from the rotor and a tubular hole extending into the rotor. The tubular hole comprises a spiral groove configured to mate with the spiral spline on the shaft. Relative rotation between the spiral spline and the spiral groove causes the rotor to linearly move along the shaft. A cam surface comprises a recession. The blade nesting in the recession constrains rotation of the rotor about the shaft in a first rotational direction, and allows linear movement of the rotor along the shaft in a second rotational direction.
B64C 27/26 - Giravions complexes, c.-à-d. aéronefs utilisant en vol à la fois les caractéristiques de l'avion et celles du giravion caractérisé par le fait qu'il est doté d'ailes fixes
B64C 27/30 - Giravions complexes, c.-à-d. aéronefs utilisant en vol à la fois les caractéristiques de l'avion et celles du giravion avec moyens permettant de réduire la traînée du rotor en période de non fonctionnement
B64C 27/50 - Pales repliables pour faciliter le rangement de l'aéronef
95.
METHOD AND APPARATUS TO IMPROVE LIFT TO DRAG RATIO OF A ROTOR BLADE
A rotor blade includes a blade member having a top side, a bottom side, a leading edge, and a trailing edge. inner surfaces of the top and bottom sides of the leading extension member adhesively are connected to the top side and the bottom side of the leading edge of the blade member. The leading edge extension member is comprised of plies of at least one of a fabric and a tape with a cured resin. The leading edge extension member is configured to extend a chord length of at least a portion of the rotor blade. The curved portion of the leading edge extension member and the leading edge of the blade member define a hollow interior portion therebetween. A method of improving a lift to drag ratio of a rotor blade is also disclosed.
An Unmanned Aerial Vehicle (UAV) has a first blade assembly configured to rotate in a first direction about an axis of rotation and a second blade assembly configured to rotate in a second direction opposite the first direction about the axis of rotation, wherein the second blade assembly can be selectively cocked relative to the axis of rotation.
B64C 27/52 - Basculement de l'ensemble du rotor par rapport au fuselage
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 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
B64C 11/48 - Ensembles de plusieurs hélices coaxiales
B64C 27/10 - Hélicoptères à plusieurs rotors disposés coaxialement
According to one embodiment, an aircraft features a fuselage, a wing member, and two fuselage beam. The fuselage features a first plurality of structural supports, a second plurality of structural supports, a first opening disposed between the first plurality of structural supports, and a second opening disposed between the second plurality of structural supports. The wing member is disposed above the first opening and above the second opening. The wing features a plurality of ribs including a first rib and a second rib. The first fuselage beam couples the first rib of the wing member to the fuselage and has an elongated body portion extending across the first plurality of structural supports. The second fuselage beam couples the second rib of the wing member to the fuselage and features an elongated body portion extending across the second plurality of structural supports.
A combined controller with a panel that has a face and a back, a case attached to the back of the panel. The face of the panel includes a plurality of first primary flight display inputs configured to receive physical inputs for the control of a first primary flight display; a plurality of second primary flight display inputs configured to receive physical inputs for the control of a second primary flight display; and a plurality of flight control inputs configured to receive physical inputs for the control of automated flight behavior.
B64D 43/00 - Aménagements ou adaptations des instruments
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
In a first aspect, there is a rotor system for a tiltrotor aircraft, the rotor system including an upper outboard engine in a fixed location on a wing member of the tiltrotor aircraft; a lower outboard engine in a fixed location on the wing member; and a prop-rotor pylon in power communication with the upper and lower outboard engines, the prop-rotor pylon being configured to selectively rotate between a vertical position and a horizontal position. In another aspect, there is provided a tiltrotor aircraft including a fuselage; a wing member; an upper outboard engine in a fixed location on the wing member; a lower outboard engine in a fixed location on the wing member; and a prop-rotor pylon in power communication with the upper and lower outboard engines, the prop-rotor pylon being configured to selectively rotate between a vertical position and a horizontal position.
B64C 29/00 - Aéronefs capables d'atterrir ou de décoller à la verticale, p. ex. aéronefs à décollage et atterrissage verticaux [ADAV, en anglais VTOL]
B64D 27/26 - Aéronefs caractérisés par la structure du montage du groupe moteur
B64D 29/02 - Nacelles, carénages ou capotages des groupes moteurs montés dans les ailes
B64D 35/08 - Transmission de la puissance des groupes moteurs aux hélices ou aux rotorsAménagements des transmissions caractérisée par le fait que la transmission est entraînée par plusieurs groupes moteurs
B64D 33/02 - Aménagement sur les aéronefs des éléments ou des auxiliaires des ensembles fonctionnels de propulsion, non prévu ailleurs des entrées d'air de combustion
B64D 27/02 - Aéronefs caractérisés par le type ou la position des groupes moteurs
An air cannon has a barrel and a sabot sized to fit within the barrel and configured to engage a projectile located within the barrel forward of the sabot. A flexible cord connects the sabot to a fixed location relative to the barrel. Forward motion of the sabot is decelerated by the cord after the sabot exits the forward end of the barrel, and the sabot is retained by the cord near the forward end of the barrel.
F41B 11/62 - Armes de tir à gaz comprimé, p. ex. armes de tir à air compriméArmes de tir à vapeur caractérisées par l’alimentation en gaz comprimé dans lesquelles la pression est fournie par une cartouche de gaz
F41F 1/00 - Appareils de lancement éjectant des projectiles à partir d'un tube, p. ex. canonsCanons lance-harpons
F41B 11/73 - Dispositions pour l’étanchéitéPistons
