A system is provided for translating sections of an icing wind tunnel to expand a size range of water droplets. The system includes: a set of actuators coupled to a set of sections of the icing wind tunnel; and a controller coupled to the set of actuators, wherein the controller is configured to: receive data relating to a water droplet generated within the icing wind tunnel; determine a directional impact on a model within the icing wind tunnel based upon the data relating to the water droplet; and adjust at least one of the set of sections of the icing wind tunnel in at least one of an up or a down direction in a subsequent test.
2.
ELECTRONIC PULSE INJECTION SYSTEM FOR AN ICING WIND TUNNEL
A system is provided for dispersing supercooled liquid water in an icing wind tunnel. The system includes a spray bar; a spray nozzle coupled to the spray bar; a pressure control valve coupled to the spray bar; and a controller coupled to the pressure control valve and the spray nozzle. The controller is configured to receive input identifying a selected liquid water content and a selected water droplet size for dispersing the supercooled liquid water in the icing wind tunnel; configure an injector duty cycle of the spray nozzle to generate the selected liquid water content; and configure the pressure control valve to generate the selected water droplet size, wherein configuring the spray nozzle and the pressure control valve disperses the supercooled liquid water in the icing wind tunnel.
3.
ELECTRO-PNEUMATIC CABLE CUTTER ASSEMBLY FOR AIRCRAFT HOIST
A cable cutter assembly for an aircraft hoist is disclosed, and includes an actuator assembly (e.g., at least one pressurized fluid cavity, a first outlet port, and a solenoid that includes a coil and an armature). The armature is movable between closed and open positions relative to the first outlet port (e.g., via an actuation force), with the armature engaging the first outlet port for the closed position (e.g., a valve seal incorporated by the armature) and being spaced from the first outlet port for the open position. A cutter body includes a cutter body cavity that is fluidly connected with the first outlet port. A cutter is movably disposed within the cutter body cavity. Disposing the armature in the open position (e.g., via energizing the coil) fluidly connects the pressurized fluid cavity with the cutter body cavity to move the cutter in a cable cutting direction.
A landing gear actuation system is disclosed herein. The landing gear actuation system includes a trunnion sprocket coupled to a movable member, a drive motor, and a flexible drive member extending between and to the motor and the trunnion sprocket. The motor is configured to move the flexible drive member, wherein the movement of the flexible drive member moves the trunnion sprocket and the movable member. The flexible drive member may be a belt or a chain.
An inspection system is disclosed herein. The inspection system includes a control system and a hub assembly. The control system includes a base having a top surface and configured to move horizontally forward and backward, an upright member extending orthogonally from the top surface of the base and configured to move vertically up and down, the upright member having a top surface, and an elongated member extending orthogonal to the upright member having a proximal end and a distal end, the proximal end connected to the top of the upright member, wherein the elongated member is configured to rotate. The hub assembly is connected to the distal end of the elongated member. The hub assembly includes a spring-loaded arm extending orthogonally from the hub assembly and a sensor connected to a distal end of the spring-loaded arm.
6.
TEMPERATURE COMPENSATED SHOCK STRUT VISUAL HEALTH INDICATOR SYSTEMS AND METHODS
A temperature compensating shock strut health indicator system for use with a shock strut comprises a visual indicator comprising a plurality of sectors and a pointer configured to rotate with respect to the visual indicator to point to one of the plurality of sectors. The sector to which the pointer points to is dependent on the shock strut stroke (i.e., the position of the piston with respect to the cylinder). In various embodiments, the visual indicator includes various rings that correspond to a different temperature compensated ideal stroke whereby a crew member can correspond the pointer to the appropriate ring depending on ambient temperature. In various embodiments, the pointer comprises a temperature sensitive material configured to cause the pointer to rotate with respect to the visual indicator to actively compensate for temperature.
B64F 5/60 - Test ou inspection des composants ou des systèmes d'aéronefs
F16F 9/00 - Ressorts, amortisseurs de vibrations, amortisseurs de chocs ou amortisseurs de mouvement de structure similaire, utilisant un fluide ou moyen équivalent comme agent d'amortissement
Systems and methods for operating a hoist and hook assembly may method comprising determining a clutch slip via a clutch sensor, determining an overload via a load sensor, and cutting a cable coupled to the hoist and hook assembly in response to the clutch slip determination and the overload determination.
ABSTRACT A hydraulic fluid system is disclosed herein. The hydraulic fluid system includes a hydraulic motor including an output shaft, a reduction gear box having a first side and an opposing second side, the reduction gear box being coupled to the output shaft at the first side and coupled to a reduction shaft at the second side, and a magneto-rheological fluid brake (MRF) brake coupled to the reduction shaft. Date Recue/Date Received 2023-04-12
F15B 13/00 - SYSTÈMES FONCTIONNANT AU MOYEN DE FLUIDES EN GÉNÉRAL; DISPOSITIFS DE MANŒUVRE FONCTIONNANT PAR PRESSION DE FLUIDE, p.ex. SERVOMOTEURS; PARTIES CONSTITUTIVES OU AMÉNAGEMENTS DES SYSTÈMES À PRESSION DE FLUIDE, NON PRÉVUS AILLEURS - Parties constitutives des systèmes de servomoteurs
F16H 61/4157 - Commande de freinage, p.ex. empêchant le passage en surrégime de la pompe lorsque le moteur fait office de pompe
F15B 15/00 - Dispositifs actionnés par fluides pour déplacer un organe d'une position à une autre; Transmission associée à ces dispositifs
F16H 47/02 - Combinaisons d'une transmission mécanique avec des embrayages à fluide ou une transmission à fluide la transmission à fluide étant du type volumétrique
A closure assembly for a fluid port having a fluid flow channel defined along an axis, the channel ending in a port opening, the closure assembly comprising: a closure cap (301) extending in a first plane arranged to seat across, and close the port opening, in use, in a closed state, a guide arm (310) extending from the cap in a second plane substantially perpendicular to the first plane; a lifting guide (601) to accommodate and retain the guide arm for movement of the guide arm in the second plane as the cap moves axially away from the opening; and a pivot mechanism (312, 314) between the guide arm and the lifting guide about which the cap is able to pivot relative to the lifting guide to an open position.
B65D 41/30 - Capuchons déformables, combinés avec des bouchons élastiques, permettant la réutilisation en tant que fermeture temporaire
B67B 1/04 - Fermeture des bouteilles, des bocaux ou des récipients analogues par application de bouchons par introduction de bouchons non filetés, p.ex. en liège
B67B 3/22 - Fermeture des bouteilles, des bocaux ou des récipients analogues par application de capsules par application de capsules "pression"
A landing gear actuation system is disclosed herein. The landing gear actuation system includes an attachment point integral to a movable member, a flexible pull member having a first end coupled to the attachment point, and a motor configured to move the flexible pull member, wherein the movement of the flexible pull member moves the attachment point and the movable member.
An aircraft wing may comprise an airfoil having deicing zone, an anti-icing zone, and an ice runback control zone. An aircraft wing may comprise an electro- thermal ice protection system disposed in the aircraft wing. The electro-thermal ice protection system may be disposed along the deicing, anti-icing, and ice runback control zones of the airfoil to improve aerodynamic performance of the aircraft and reduce ice formation along the wings of the aircraft.
Ice may form along the leading edge of an aircraft wing or horizontal and vertical stabilizers. A pneumatic deicer system may be configured to inflate and dislodge ice along the leading edge of lift and control surfaces. The pneumatic deicer system may comprise a laser welded deicing boot attached to the leading edge. The compressed air can be directed to the deicing boot, inflating the deicing boot along inflatable tubes formed by laser welds, which can crack and dislodge the ice. A method of manufacturing a laser welded pneumatic deicer boot is also disclosed.
B64D 15/16 - Dégivrage ou antigivre des surfaces externes des aéronefs par dispositifs mécaniques, p.ex. des gaines ou des bourrelets fixés ou incorporés à la surface et soumis à des pulsations
Ice may form along the leading edge of an aircraft wing. A pneumatic deicing system may be configured to crack and dislodge ice along the leading edge of the wing. The pneumatic deicing system may comprise a deicing boot assembly haying a deicing boot attached to the leading edge, and a gas generator fluidly coupled to the deicing boot assembly. The gas generator may comprise a propellant and may decompose the propellant, liberating a compressed gas. The compressed gas may be directed to the deicing boot assembly, inflating the deicing boot, which may crack and dislodge the ice.
B64D 15/18 - Dégivrage ou antigivre des surfaces externes des aéronefs par dispositifs mécaniques, p.ex. des gaines ou des bourrelets fixés ou incorporés à la surface et soumis à des pulsations la surface étant un profil d'aile, un rotor ou une hélice
F23R 5/00 - Chambres de combustion à combustion continue utilisant du combustible solide ou pulvérulent
14.
SYSTEMS AND METHODS FOR MANUFACTURING LANDING GEAR COMPONENTS USING TITANIUM
A metallic part is disclosed. The part may comprise a functionally graded monolithic structure characterized by a variation between a first material composition of a tubular preform and a second material composition of at least one of a secondary structural element wherein each of the first material composition and the second material composition comprises at least one of a titanium metal or an alloy of titanium. The first material composition may comprise an alpha-beta titanium alloy. The second material composition may comprise a beta titanium alloy.
B22F 5/12 - Fabrication de pièces ou d'objets à partir de poudres métalliques caractérisée par la forme particulière du produit à réaliser de tubes ou de fils
B22F 3/115 - Fabrication de pièces ou d'objets à partir de poudres métalliques, caractérisée par le mode de compactage ou de frittage; Appareils spécialement adaptés à cet effet par pulvérisation de métal fondu, c.à d. frittage par pulvérisation, moulage par pulvérisation
B22F 3/16 - Compactage et frittage par des opérations successives ou répétées
B23K 20/12 - Soudage non électrique par percussion ou par une autre forme de pression, avec ou sans chauffage, p.ex. revêtement ou placage la chaleur étant produite par friction; Soudage par friction
A composite component may be additively manufactured by a system that mixes a fiber and matrix and extrudes a body made of the fiber and matrix toward a work piece. The extruded body may be pressed against the work piece and the workpiece and/or extruded body may be moved relative to the other. The extruded body may at least partially melt and flow, uniting with the workpiece and additively manufacturing a layer of a feature thereon. In this manner, friction stir additive manufacturing of composite components having a fiber and matrix composite may be accomplished.
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 70/12 - 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 courtes, p.ex. sous forme d'un mat
16.
INTEGRAL STEERING MOTOR AND COLLAR FOR LANDING GEAR
A steering apparatus may comprise a steering collar, a first linear actuator, a first drive gear, a crankshaft, and a sun gear, wherein the sun gear is disposed within the collar, wherein the first drive gear is fixed to the crankshaft and coupled to the sun gear such that the collar rotates about the sun gear in response to rotation of the crankshaft, wherein the first linear actuator is coupled between the crankshaft and the collar.
B62D 5/06 - Direction assistée ou à relais de puissance à fluide, c. à d. au moyen d'un fluide sous pression produisant toute la force nécessaire, ou la plus grande partie de celle-ci, pour commander la direction du véhicule
17.
METHODS, SYSTEMS, AND APPARATUS FOR COMPONENT MANUFACTURING
Methods, systems, and apparatuses for component manufacturing are provided. A component may be manufactured via an extrusion of loose substrate material into a unitary tubing. Features may be added to the tubing via friction stir additive manufacturing to manufacture a component. In this manner, a component may be manufactured from titanium alloys while processing challenges such as iron segregation or material loss through machining are ameliorated. Such a component may replace steel or other high strength components and further exhibits corrosion resistance.
B22F 5/12 - Fabrication de pièces ou d'objets à partir de poudres métalliques caractérisée par la forme particulière du produit à réaliser de tubes ou de fils
B33Y 30/00 - Appareils pour la fabrication additive; Leurs parties constitutives ou accessoires à cet effet
B33Y 70/00 - Matériaux spécialement adaptés à la fabrication additive
B22F 3/20 - Fabrication de pièces ou d'objets à partir de poudres métalliques, caractérisée par le mode de compactage ou de frittage; Appareils spécialement adaptés à cet effet par extrusion
B23K 20/12 - Soudage non électrique par percussion ou par une autre forme de pression, avec ou sans chauffage, p.ex. revêtement ou placage la chaleur étant produite par friction; Soudage par friction
An aircraft actuation system is disclosed that includes a pair of cylinders, a piston movably disposed in each cylinder, and a roller train that extends between the pistons in the two cylinders. A portion of the roller train is disposed beyond the cylinders to engage a pinion. Movement of the pistons in the two cylinders in opposite directions produces a corresponding movement of the roller train to in turn rotate the pinion. The roller train may be maintained in compression between its two ends by fluid pressure exerted on a common face of each of the pistons in the two cylinders. The cylinders may be disposed in non-colinear relation, including in parallel relation to one another. A guide may be used to maintain rollers of the roller train in a proper orientation for entry into a space between an outer race and the pinion.
F15B 15/06 - Schéma mécanique de montage caractérisé par les moyens transformant le mouvement de l'élément entraîné par le fluide en mouvement de l'organe terminal qui est actionné pour la transformation mécanique d'un mouvement rectiligne en un mouvement non rectiligne
An aircraft landing gear actuation system which uses two separate actuation forces to retract aircraft landing gear is disclosed. One of the actuation forces may be provided by an actuator, such as a hydraulic actuator. Another of these actuation forces may be provided by a pressurized fluid that is directed into the actuator through a conduit that extends into a hollow interior of an actuator rod of the actuator. The pressurized fluid may be provided from a pressurized fluid source that contains a fixed volume of pressurized fluid. This pressurized fluid may exert a force on an actuator piston of the actuator or the actuator rod. The pressurized fluid may also be used to dampen the deployment of the landing gear.
A method is provided for producing ultra-fine-grained materials using additive manufacturing. The method includes commanding, by a controller, a laser device to produce a plurality of optical pulses to a base material to add an additive material to the base material. The method further includes commanding, by the controller, a vibration mechanism to vibrate the base material as the plurality of optical pulses are being applied to the base material forming fine equiaxed grains with random crystallographic texture in the base material.
B29C 64/153 - Procédés de fabrication additive n’utilisant que des matériaux solides utilisant des couches de poudre avec jonction sélective, p.ex. par frittage ou fusion laser sélectif
B33Y 40/00 - Opérations ou équipements auxiliaires, p.ex. pour la manipulation de matériau
B22F 10/38 - Commande ou régulation des opérations pour obtenir des caractéristiques spécifiques du produit, p.ex. le lissage de la surface, la densité, la porosité ou des structures creuses
B22F 10/50 - Traitement des pièces ou des articles pendant leur formation, p.ex. traitements appliqués aux couches fusionnées pendant leur formation
Disclosed is a method of manufacturing a stainless steel component, the method including texturizing a stainless steel substrate by bead blasting to provide a texturized stainless steel. The stainless steel substrate includes grade 316 austenitic stainless steel. The method also includes treating the texturized stainless steel with a passivation solution to provide a passivated stainless steel. The method further includes treating the passivated stainless steel with an oxidizing solution including sulfuric acid and hydrogen peroxide at a temperature of about 130 to about 200 degrees Fahrenheit for at least 50 minutes to provide an antimicrobial stainless steel surface that is free of a separate coating. The method includes obtaining at least 99.9% E. coli reduction as measured by JIS Z 2801:2010 test on the antimicrobial stainless steel without a separate coating.
C23F 17/00 - Procédés à étapes multiples pour le traitement de surface de matériaux métalliques utilisant au moins un procédé couvert par la classe et au moins un procédé couvert soit par la sous-classe , soit par la sous-classe , soit par la classe
B05D 5/02 - Procédés pour appliquer des liquides ou d'autres matériaux fluides aux surfaces pour obtenir des effets, finis ou des structures de surface particuliers pour obtenir une surface mate ou rugueuse
B24C 1/10 - Méthodes d'utilisation de jet abrasif en vue d'effectuer un travail déterminé; Utilisation d'équipements auxiliaires liés à ces méthodes pour augmenter la compacité des surfaces, p.ex. par grenaillage
A shimmy damper assembly may comprise: a damper piston including a piston head, the piston head comprising a first permanent magnet, a shimmy cylinder including a second permanent magnet disposed on an axial surface of the shimmy cylinder, and a gland nut coupled to the shimmy cylinder, the gland nut including a third permanent magnet spaced apart axially from the second permanent magnet, the piston head disposed between the first permanent magnet and the second permanent magnet.
A rack assembly for a rack and pinion gear system may comprise: a rack housing; and a rack disposed within the rack housing, the rack and the rack housing at least partially defining a first hydraulic chamber disposed between a first side of the rack and the rack housing, a second hydraulic chamber disposed between a second side of the rack and the rack housing, a third hydraulic chamber disposed within the rack proximal the first hydraulic chamber, and a fourth hydraulic chamber disposed within the rack proximal the second hydraulic chamber.
F16H 47/02 - Combinaisons d'une transmission mécanique avec des embrayages à fluide ou une transmission à fluide la transmission à fluide étant du type volumétrique
B62D 3/12 - Boîtiers de direction mécaniques du type à crémaillère
B64C 25/50 - Atterrisseurs orientables; Amortissement du shimmy
F16H 19/04 - Transmissions comportant essentiellement et uniquement des engrenages ou des organes de friction et qui ne peuvent transmettre un mouvement rotatif indéfini pour convertir un mouvement rotatif en mouvement alternatif et vice versa comportant une crémaillère et pignon
24.
SYSTEMS AND METHODS FOR HIGH STRENGTH TITANIUM ROD ADDITIVE MANUFACTURING
A method of forming a rod feedstock for titanium stir friction welding additive manufacturing may comprise: mixing a plurality of powdered metals comprising titanium, iron, vanadium, and aluminum to produce a powder blend; at least one of die pressing the powder blend to fomi a die pressed powder or continuously powder rolling the powder blend to form a die pressed powder; and sintering the powder blend to form a rod feedstock having a cross-sectional profile.
B22F 3/16 - Compactage et frittage par des opérations successives ou répétées
B33Y 70/00 - Matériaux spécialement adaptés à la fabrication additive
B29C 64/153 - Procédés de fabrication additive n’utilisant que des matériaux solides utilisant des couches de poudre avec jonction sélective, p.ex. par frittage ou fusion laser sélectif
B22F 5/12 - Fabrication de pièces ou d'objets à partir de poudres métalliques caractérisée par la forme particulière du produit à réaliser de tubes ou de fils
25.
SYSTEMS AND METHODS FOR HIGH STRENGTH TITANIUM ROD ADDITIVE MANUFACTURING
A method of titanium rod additive manufacturing may comprise: mixing a plurality of powdered metals comprising titanium, iron, vanadium, and aluminum to produce a powder blend; isostatic pressing the powder blend to form a billet having a cross-sectional profile; cutting the billet to form a rod feedstock having the first cross-sectional profile; loading the rod feedstock into an additive manufacturing machine configured to deposit the rod feedstock; and producing a metallic component from the rod feedstock.
B33Y 70/00 - Matériaux spécialement adaptés à la fabrication additive
B33Y 80/00 - Produits obtenus par fabrication additive
B22F 5/12 - Fabrication de pièces ou d'objets à partir de poudres métalliques caractérisée par la forme particulière du produit à réaliser de tubes ou de fils
B23K 20/12 - Soudage non électrique par percussion ou par une autre forme de pression, avec ou sans chauffage, p.ex. revêtement ou placage la chaleur étant produite par friction; Soudage par friction
26.
GYROSCOPE ASSISTED HELICOPTER RESCUE LIFT SYSTEMS AND METHODS
A patient litter basket spin control assembly includes a first gyroscope and a motion sensor for sensing an angular acceleration of a patient litter basket. The first gyroscope generates a counter torque to the litter basket to slow the angular acceleration of the litter basket to provide stabilization. The first gyroscope and a second gyroscope may be configured as a pair and located at opposite ends of the litter basket.
B64D 1/00 - Largage, éjection ou réception, en cours de vol, d'objets, de liquides ou similaires
A62B 1/00 - Dispositifs pour faire descendre des personnes hors des bâtiments ou dans des situations analogues
B66C 13/06 - Dispositifs auxiliaires pour commander les mouvements des charges suspendues ou pour empêcher le câble de prendre du mou pour limiter ou empêcher le balancement longitudinal ou transversal des charges
27.
SYSTEMS AND METHODS FOR DIRECT DEPOSITION OF THIXOTROPIC ALLOYS
A method may comprise: placing a probe in a molten metal melt comprising a thixotropic metal alloy; injecting a gas into the molten metal melt to form a saturated slurry, the saturated slurry being at a temperature above a liquidus temperature of the thixotropic metal alloy after injecting the gas; removing the probe from the molten metal melt; and depositing the molten metal melt through an extruder of an additive manufacturing system.
A torque transfer assembly comprising a drive shaft (4) and a driven shaft (10) and a dielectric insert (20) arranged to be positioned between the drive shaft and the driven shaft, the insert assembly comprising a body of dielectric material shaped to form an insulating layer and configured to engage, respectively, with a first shaped engagement feature (15) on the drive shaft and a second shaped engagement feature (16) on the driven shaft, in torque transfer engagement, the insulating layer providing a dielectric barrier between the drive shaft and the driven shaft.
F16D 3/74 - Accouplements extensibles, c. à d. avec moyens permettant le mouvement entre parties accouplées durant leur entraînement avec pièces d'accouplement reliées par un ou plusieurs organes intermédiaires avec des fixations aux pièces d'accouplement axialement espacées l'organe ou les organes intermédiaires étant en caoutchouc ou faits d'un autre matériau flexible
F16K 51/00 - Autres détails non particuliers aux types de soupapes ou clapets ou autres appareils d'obturation
A dielectric insulating assembly arranged to be positioned between a drive shaft (4) and a driven shaft (10) of a motorised drive assembly, the assembly comprising dielectric insulation (5) between the drive shaft and the driven shaft and plurality of electrically non-conductive fastener elements (6) configured to connect the drive shaft to the driven shaft and the dielectric insulation therebetween, in torque transfer engagement, the fasteners located around an outer boundary of the dielectric insulation.
F16D 3/56 - 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 lamelles métalliques élastiques, des bielles élastiques ou des éléments analogues, p.ex. disposés radialement ou parallèlement à l'axe, les organes étant soumis ensemble à un effet de cisaillement sous l'action de la charge totale
F16D 1/033 - Accouplements pour établir une liaison rigide entre deux arbres coaxiaux ou d'autres éléments mobiles d'une machine pour liaison bout à bout de deux arbres ou de deux pièces analogues par serrage de deux surfaces perpendiculaires à l'axe de rotation, p.ex. avec des brides boulonnées
F16D 1/076 - Accouplements pour établir une liaison rigide entre deux arbres coaxiaux ou d'autres éléments mobiles d'une machine pour montage d'un organe sur un arbre ou à l'extrémité d'un arbre par serrage de deux surfaces perpendiculaires à l'axe de rotation, p.ex. avec des brides boulonnées
F16K 51/00 - Autres détails non particuliers aux types de soupapes ou clapets ou autres appareils d'obturation
A clamp assembly comprising a plurality of clamps (20, 30) each comprising two clamp arms (21, 22, 31, 32) pivotal relative to each other about a hinge point (23, 33), and a common connector part (40) joining two or more of said clamps to each other at their hinge points.
F16B 2/10 - Brides ou colliers, c. à d. dispositifs de fixation dont le serrage est effectué par des forces effectives autres que la résistance à la déformation inhérente au matériau dont est fait le dispositif externes c. à d. agissant par contraction utilisant des mâchoires sur pivot
F16L 23/036 - Raccords à brides les brides étant raccordées par des organes tendus axialement caractérisés par les moyens de mise en tension, p.ex. colliers de serrage en forme de C ou boulons spécialement adaptés
F16M 13/02 - Autres supports ou appuis pour positionner les appareils ou les objets; Moyens pour maintenir en position les appareils ou objets tenus à la main pour être portés par un autre objet ou lui être fixé, p.ex. à un arbre, une grille, un châssis de fenêtre, une bicyclette
A valve assembly comprising a movable valve element (3) arranged to move relative to a valve housing (30) between an open and a closed position, the valve housing including a drainage body (40) provided with drainage holes (41, 42) arranged to allow fluid to drain from the valve assembly from gaps (10, 11, 12) between the movable valve element and the housing via the drainage holes.
F16K 27/00 - Structures des logements; Matériaux utilisés à cet effet
F16K 24/02 - Dispositifs, p.ex. soupapes, pour la mise à l'air libre ou l'aération d'enceintes l'enceinte constituant elle-même une soupape, un robinet ou une vanne
F16K 51/00 - Autres détails non particuliers aux types de soupapes ou clapets ou autres appareils d'obturation
A connector assembly comprising: a first connector part (100) and a second connector part (200), each connector part defining a fluid flow passage therethrough configured to together define a fluid flow conduit when the first and second parts are connected together, the connector assembly further comprising an extension part (500) mounted around one of the first and the second connector parts, the extension part (500) arranged to move relative to the connector part around which it is mounted to extend across an interface area between the first connector part and the second connector part and to bridge the first and second connector parts when the first and second connector parts are brought to meet each other to define the fluid conduit.
F16L 21/02 - Raccords avec manchon ou douille avec segments d'étanchéité élastiques entre le tuyau et le manchon ou entre le tuyau et la douille, p.ex. avec des segments roulants ou autres segments profilés préfabriqués
F16L 21/08 - Raccords avec manchon ou douille avec moyens additionnels de verrouillage
33.
MECHANICAL ICE PROTECTION SYSTEM FOR AERODYNAMIC SURFACES
An ice protection system adapted to protect at least one ice-susceptible flight surface of an aircraft includes a mechanical ice protection device attached to the flight surface. A controller controls a power source that causes the mechanical ice protection device to change in shape and, thereby, change an aerodynamic characteristic of the flight surface. This change in shape happens only when the current thickness of ice on the surface exceeds a minimum thickness.
B64D 15/16 - Dégivrage ou antigivre des surfaces externes des aéronefs par dispositifs mécaniques, p.ex. des gaines ou des bourrelets fixés ou incorporés à la surface et soumis à des pulsations
F03D 80/40 - Détection de givre; Moyens de dégivrage
B64D 15/20 - Dispositifs pour détecter le givrage ou amorcer la mise en action du dégivrage
F25C 5/06 - Appareils pour concasser, enlever ou recueillir la glace sans utiliser de scies au moyen de corps se déformant, avec lesquels la glace est en contact, p.ex. en utilisant des éléments gonflables
A ball valve assembly comprising a ball element (11) arranged to be rotated by rotation of a shaft (110) in engagement with the ball element, the ball element having first (12) and second (13) flow channels defined therethrough, a first inlet port (12a) at a first end of said first flow channel, a first outlet port (12b) at a second end of the first channel, a second inlet port (13a) at a first end of the second flow channel and a second outlet port (13b) at a second end of the second channel.
F16K 11/087 - Soupapes ou clapets à voies multiples, p.ex. clapets mélangeurs; Raccords de tuyauteries comportant de tels clapets ou soupapes; Aménagement d'obturateurs et de voies d'écoulement spécialement conçu pour mélanger les fluides dont toutes les faces d'obturation se déplacent comme un tout comportant uniquement des robinets à boisseau à noix sphérique
F16K 5/06 - Robinets à boisseau consistant seulement en un dispositif obturateur dont au moins une des faces d'obturation a la forme d'une surface de solide de révolution plus ou moins complète, le mouvement d'ouverture et de fermeture étant essentiellement rota dont les boisseaux sont à surface sphérique; Leurs garnitures d'étanchéité
F16K 37/00 - Moyens particuliers portés par ou sur les soupapes ou autres dispositifs d'obturation pour repérer ou enregistrer leur fonctionnement ou pour permettre de donner l'alarme
35.
LASER INDUCED GRAPHENE AS PRETREATMENT TO PLATE NON-CONDUCTIVE COMPOSITES
A method of manufacture can comprise: treating a surface of a polymeric substrate with a laser induced graphene; and bonding a metallic layer to the laser induced graphene.
A cable tensioning capstan assembly comprises a capstan drum and at least a first traction flange. The capstan drum may be configured to support a cable (e.g., a cable is configured to wrap around the capstan drum), and the capstan drum may be configured to rotate about an output axis. The first traction flange may be disposed adjacent the first axial end of the capstan drum and configured to rotate about the output axis. In various embodiments, the first traction flange is independently rotatable relative to the capstan drum. A clutch assembly between an input shaft and the first traction flange may facilitate the independent rotatability of the first traction flange.
A wheel retaining assembly for a landing gear having an axle and an outer wheel bearing, the axle defining an axial direction along an axial centerline, is disclosed. In various embodiments, the wheel retaining assembly includes a first wheel spacer configured to slide over the axle and to abut the outer wheel bearing, the first wheel spacer having an axially outward portion; and a second wheel spacer configured to slide over the axle, the second wheel spacer having an axially inward portion configured to engage the axially outward portion of the first wheel spacer.
A nose-wheel steering system may comprise an actuator and a bevel gear rotationally coupled to a drive shaft of the actuator. The bevel gear may be configured to rotate about a first axis. A collar gear may be intermeshed with the bevel gear. The collar gear may be configured to rotate about a second axis that is generally perpendicular to the first axis.
B64C 25/50 - Atterrisseurs orientables; Amortissement du shimmy
B62D 5/06 - Direction assistée ou à relais de puissance à fluide, c. à d. au moyen d'un fluide sous pression produisant toute la force nécessaire, ou la plus grande partie de celle-ci, pour commander la direction du véhicule
A method of determining whether a landing event of an aircraft is hard may comprise: receiving, by a controller via a stroke position sensor, a stroke profile as a function of time for a shock strut; receiving, by the controller via a gas pressure sensor, a gas pressure in a gas chamber of the shock strut; receiving, by the controller via a wheel speed sensor, a wheel speed of a tire in a landing gear assembly; calculating, by the controller, multiple time dependent functions based on the stroke profile of the shock strut, based on the gas pressure, a shock strut temperature, and the wheel speed; and comparing, by the controller, the multiple time dependent functions to respective predetermined thresholds to determine whether the landing event is hard.
B64F 5/00 - Tracé, fabrication, assemblage, nettoyage, entretien ou réparation des aéronefs, non prévus ailleurs; Manipulation, transport, test ou inspection de composants d’aéronefs, non prévus ailleurs
ABSTRACT A shock strut assembly for a landing gear may comprise a strut cylinder, a strut piston configured to telescope relative to the strut cylinder, and a locking system. The locking system may be configured to restrict rotation of the strut piston relative to the strut cylinder in response to compression of the shock strut assembly. Date Recue/Date Received 2021-11-12
A snubber assembly may comprise a snubber having a snubber body with an inner diameter surface and an outer diameter surface, the snubber including a plurality of valve receptacles disposed in the outer diameter surface, the snubber including a plurality of radial apertures disposed through the snubber body, each radial aperture in the plurality of radial apertures disposed in a respective valve receptacle in the plurality of valve receptacles; and a plurality of restrictor valves, each restrictor valve in the plurality of restrictor valves disposed in a respective valve receptacle in the plurality of valve receptacles, each restrictor valve in the plurality of restrictor valves including an orifice disposed through a blade.
F16F 9/512 - Moyens réagissant à l'action de la charge sur l'amortisseur ou à la pression de fluide dans l'amortisseur
F16F 9/516 - Dispositifs particuliers de réglage automatique de l'amortisseur aboutissant à des effets d'amortissement à la compression différents des effets d'amortissement à l'extension
A shaft assembly includes a composite tube and an impact shield. The composite tube has a longitudinal centerline axis and the impact shield may be disposed around the composite tube and may extend along a length of the composite tube. A gap may be defined between the composite tube and the impact shield. Generally, shaft assembly is configured to inhibit impact damage to the composite tube and/or facilitate visual detection of damage from impacts. The shaft assembly may further include a shock absorbing sleeve disposed in the gap between the composite tube and the impact shield.
A system may comprise a main host device; a first splitter having a first input port, a first output port, and a second output port, the first input port configured for electronic communication with the main host device; a first local display monitor configured for electronic communication with the first output port of the first splitter; a first video capture device configured for electronic communication with the second output port of the first splitter; a multi-cam switch having a plurality of input ports and an outlet port; a second splitter having a second input port, a third output port, and a fourth output port, the outlet port of the multi-cam switch configured for electronic communication with the second input port; and a second video capture device configured for electronic communication with the third output port.
An uplock system includes a cam plate comprising a cam channel, a hook configured to rotate with respect to the cam plate, a follower rotatably coupled to the hook, wherein a portion of the follower moves within the cam channel in response to rotation of the hook, a stopper configured to engage the follower, and a first biasing member configured to bias the stopper towards the follower to stop the follower from moving within the cam channel, thereby locking the hook in a locked position.
A damping mechanism may comprise a housing, a shaft, a spring arm assembly including a first spring arm, wherein the spring arm assembly is coupled to the shaft and configured to rotate in response to a rotation of the shaft, wherein the first spring arm extends relatively radially outward of the spring arm assembly toward the housing in response to the rotation of the shaft, and wherein the rotation of the shaft is damped in response to extending the first spring arm.
F16F 15/121 - Suppression des vibrations dans les systèmes rotatifs par utilisation d'organes mobiles avec le système lui-même utilisant des organes élastiques ou des organes amortisseurs de friction, p.ex. entre un arbre en rotation et une masse giratoire montée dessus utilisant des ressorts comme organes élastiques, p.ex. des ressorts métalliques
A shock strut is disclosed. The shock strut may include a shock strut cylinder, a shock strut piston that is slidably disposed within the shock strut cylinder, a metering pin, and a percolation seal configured to restrict a flow of liquid between the shock strut cylinder and the shock strut piston.
A system and various methods for determining a center of mass of an aircraft with a plurality of shock strut assemblies is illustrated. Multiple sensors, including a gas pressure sensor, and/or a position sensor, may be used to gather data and determine the center of mass of the aircraft. Various methods illustrated herein may evaluate the center of mass relative to a wheelbase axis and a wheel tread axis based on the gathered data.
A dual-sleeve, locking adjustment arrangement includes a position-sensitive component comprising an aperture, an outer eccentric sleeve disposed in the aperture, and an inner eccentric sleeve disposed in the outer sleeve. Rotation of the outer sleeve with respect to the position-sensitive component and the inner sleeve drives rotation of the position-sensitive component to adjust an angular position of the component.
F16B 19/02 - Chevilles ou manchons pour positionner les parties de machines, p.ex. goupilles coniques à encoche, goupilles de montage, manchons, bagues excentriques d'ajustement
F16B 35/00 - Boulons filetés; Boulons d'ancrage; Goujons filetés; Vis; Vis de pression
A system for use with a tripod landing gear assembly of an aircraft may comprise: a tension strut assembly having a tension strut extending from an upper end to a lower end; a drag brace assembly having an upper brace and a lower brace, the upper brace pivotably coupled to the lower brace at a center point, the lower brace rotatably coupled to the lower end of the tension strut; and a jury linkage pivotally coupled to the drag brace assembly at the center point rotatably coupled to a middle portion of the tension strut, the middle portion between the upper end and the lower end
A system for servicing a shock strut may comprise a system controller and a tangible, non-transitory memory configured to communicate with the system controller. The tangible, non-transitory memory may have instructions stored thereon that, in response to execution by the system controller, cause the system controller to perform operations, which may comprise: receiving, by the system controller, a hydraulic fluid volume difference or a pressurized gas volume difference from a ground support controller; determining, by the system controller, a desired fluid flow rate based on the hydraulic fluid volume difference or the pressurized gas volume difference; and outputting, by the system controller, a desired fluid flow rate signal corresponding to the desired fluid flow rate to at least one of a hydraulic fluid flow controller or a pressurized gas flow controller.
F16F 9/06 - Ressorts, amortisseurs de vibrations, amortisseurs de chocs ou amortisseurs de mouvement de structure similaire, utilisant un fluide ou moyen équivalent comme agent d'amortissement utilisant à la fois un gaz et un liquide
F16F 9/43 - Dispositions de remplissage, p.ex. pour l'alimentation en gaz
51.
CONTINUOUS STACKED DUAL WRAP TUBE END CLOSURE FOR ANTI-ICING SYSTEMS
An anti-icing system may comprise a deicing boot of an elastomeric material comprising a plurality of tubes, wherein the deicing boot comprises a first set of tubes and a second set of tubes, wherein each of the first set of tubes and the second set of tubes have a corresponding end, and wherein the corresponding end is coupled to a continuous dual wrap end closure.
B64D 15/16 - Dégivrage ou antigivre des surfaces externes des aéronefs par dispositifs mécaniques, p.ex. des gaines ou des bourrelets fixés ou incorporés à la surface et soumis à des pulsations
B64D 15/20 - Dispositifs pour détecter le givrage ou amorcer la mise en action du dégivrage
ABSTRACT A shimmy damper for centering a landing gear includes a cap and a housing. The shimmy damper further includes a damper shaft extending from the cap to the housing. The shimmy damper further includes a plurality of magnets configured to exert an opposing force on the cap and the housing via the damper shaft, providing a centering mechanism of the damper shaft within the housing. This centering action in turn provides for the centering of the landing gear during flight. 14 Date Recue/Date Received 2021-03-17
A system for controlling landing gear subsystems may comprise a controller and a first motor drive unit in operable communication with the controller. A first electric motor and a second electric motor may be in operable communication with the first motor drive unit. A second motor drive unit may be in operable communication with the controller. A third electric motor and a fourth electric motor may be in operable communication with the second motor drive unit. An AC/DC converter may be electrically coupled to the first drive unit and the second motor drive unit.
A nose-wheel steering system is disclosed. In various embodiments, the system includes an actuator; a strut; and a gearing mechanism operably coupling the actuator to the strut, the gearing mechanism including a steering collar attached to the strut, and idler gear engaged with the actuator and a pinion having a first gear engaged with the idler gear and a second gear engaged with the steering collar.
A landing gear system for an aircraft is disclosed. In various embodiments, the system includes a truss frame pivotally connected to a frame of the aircraft and configured to rotate about an axis; a retraction actuator configured to rotate the truss frame about the axis; a first truss link pivotally connected to the truss frame; a second truss link pivotally connected to the first truss link; a truss locking link pivotally connected to the truss frame and to the second truss link; and an articulation actuator configured to pivot the first truss link with respect to the truss frame.
B64C 25/10 - Atterrisseurs non fixes, p.ex. largables escamotables, repliables ou ayant un mouvement apparenté
B64C 25/34 - Trains d'atterrissage caractérisés par les éléments de contact avec le sol ou une surface analogue du type à roues, p.ex. bogies à roues multiples
- 9 - ABSTRACT ICE DETECTION ARRANGEMENT An ice detection system for an aircraft surface, comprising a sensor assembly (10) comprising a plurality of temperature sensitive elements configured to be arranged at respective points on the aircraft surface, a control unit (20) arranged to receive signals indicative of a temperature sensed by each of the temperature sensitive elements, a signal conducting bus (50) to transmit the signals from the temperature sensitive elements to the control unit, and means for providing power to the sensor assembly, wherein the sensor assembly further comprises a multiplexer (40) arranged to multiplex the signals from the plurality of temperature sensitive elements into a single signal for transmission on the signal conducting bus to the control unit. [FIG. 2] Date Recue/Date Received 2021-01-15
B64D 15/20 - Dispositifs pour détecter le givrage ou amorcer la mise en action du dégivrage
G01K 7/16 - Mesure de la température basée sur l'utilisation d'éléments électriques ou magnétiques directement sensibles à la chaleur utilisant des éléments résistifs
AB STRACT A carbon allotrope element includes a carbon allotrope layer formed from a carbon allotrope material impregnated with a dielectric resin and haying a first surface. The carbon allotrope element further includes a first bus bar in communication with the first surface, and a second bus bar in communication with the first surface and non-adjacent to the first bus bar. The first surface includes a layer of the dielectric resin and a plurality of abraded regions, and each of the first and second bus bars is in communication with one of the plurality of abraded regions of the first surface. 13 Date Recue/Date Received 2020-11-10
H01B 1/04 - Conducteurs ou corps conducteurs caractérisés par les matériaux conducteurs utilisés; Emploi de matériaux spécifiés comme conducteurs composés principalement soit de compositions à base de carbone-silicium, soit de carbone soit de silicium
B82Y 30/00 - Nanotechnologie pour matériaux ou science des surfaces, p.ex. nanocomposites
C08L 101/12 - Compositions contenant des composés macromoléculaires non spécifiés caractérisées par des propriétés physiques, p.ex. anisotropie, viscosité ou conductivité électrique
H05B 3/14 - Eléments chauffants caractérisés par la composition ou la nature des matériaux ou par la disposition du conducteur caractérisés par la composition ou la nature du matériau conducteur le matériau étant non métallique
ABSTRACT A heating element and conductive element system may include a heater conductive element and a heating element. The heater conductive element and the heating element may be integral components. The heater conductive element and the heating element may be discrete components. The heater conductive element may be configured for enhanced mechanical fatigue compared to typical conductive element. 19 Date Recue/Date Received 2021-01-11
H05B 3/06 - Eléments chauffants combinés constructivement avec des éléments d'accouplement ou avec des supports
B82Y 30/00 - Nanotechnologie pour matériaux ou science des surfaces, p.ex. nanocomposites
B64D 15/12 - Dégivrage ou antigivre des surfaces externes des aéronefs par chauffage électrique
H05B 3/14 - Eléments chauffants caractérisés par la composition ou la nature des matériaux ou par la disposition du conducteur caractérisés par la composition ou la nature du matériau conducteur le matériau étant non métallique
ABSTRACT A steering system may include a gear assembly and a collar. The gear assembly may include a planet carrier, a planet gear, an internal ring gear, and a sun gear. The planet gear may be disposed between the internal ring gear and the sun gear. The gear assembly may provide a mechanical advantage to the steering system, which may result in a greater powered steering range, a shorter rack assembly, and/or increased design space relative to typical steering systems. Date Recue/Date Received 2021-01-06
ABSTRACT A damping actor selector may be configured to transition a multi-actor damping system from a first damping actor configuration to a second damping actor configuration. The multi- actor damping system may be used in a shock strut assembly to alter a damping curve of the shuck strut assembly. The damping actor selector may be coupled to a metering pin of a shock strut assembly. The damping actor selector may be configured to rotate the metering pin to transition the multi-actor damping system from a first damping actor configuration to a second damping actor configuration. The first damping actor configuration may correspond to a first damping curve. The second damping actor configuration may correspond to a second damping curve. The first damping curve being different than the second damping curve. 41 Date Recue/Date Received 2021-01-11
F16F 9/44 - Ressorts, amortisseurs de vibrations, amortisseurs de chocs ou amortisseurs de mouvement de structure similaire, utilisant un fluide ou moyen équivalent comme agent d'amortissement - Parties constitutives de tels dispositifs combinés avec la correction de température
ABSTRACT A main orifice plate assembly may be configured to transition a multi-actor damping system from a first damping actor configuration to a second damping actor configuration. The multi-actor damping system may be used in a shock strut assembly to alter a damping curve of the shuck strut assembly. The main orifice plate assembly may be a part of a main orifice assembly including an orbital cam. The main orifice plate may include a flow restrictor. The flow restrictor may be configured to retract or deploy in response to main orifice plate rotating about the orbital cam. The first damping actor configuration may correspond to a first damping curve. The second damping actor configuration may correspond to a second damping curve. The first damping curve being different than the second damping curve. 42 Date Recue/Date Received 2021-01-11
F16F 9/34 - Structure des clapets particuliers; Forme ou structure des passages d'étranglement
B64C 9/34 - Surfaces ou éléments de commande réglables, p.ex. gouvernes de direction repliables ou escamotables contre ou à l'intérieur d'autres surfaces ou d'autres éléments
F16F 9/44 - Ressorts, amortisseurs de vibrations, amortisseurs de chocs ou amortisseurs de mouvement de structure similaire, utilisant un fluide ou moyen équivalent comme agent d'amortissement - Parties constitutives de tels dispositifs combinés avec la correction de température
ABSTRACT A metering pin for use in a multi-actor damping system is disclosed herein. The multi-actor damping system may be used in a shock strut assembly to alter a damping curve of the shuck strut assembly. The metering pin may be configured to transition the multi-actor damping system from a first damping actor configuration to a second damping actor configuration. The first damping actor configuration may correspond to a first damping curve. The second damping actor configuration may correspond to a second damping curve. The first damping curve being different than the second damping curve. 42 Date Recue/Date Received 2021-01-11
F16F 9/44 - Ressorts, amortisseurs de vibrations, amortisseurs de chocs ou amortisseurs de mouvement de structure similaire, utilisant un fluide ou moyen équivalent comme agent d'amortissement - Parties constitutives de tels dispositifs combinés avec la correction de température
63.
SYSTEMS FOR HARVESTING ROTATIONAL WHEEL ENERGY FOR LANDING GEAR RETRACTION
AB STRACT A system for extracting energy for landing gear retraction may comprise a wheel pump rotationally coupled to a wheel via a pinion gear. A landing gear control valve assembly may be fluidly coupled to an output of the wheel pump. A secondary pump may be fluidly coupled to the landing gear control valve assembly, and an electric motor may be operationally coupled to the secondary pump. Date Recue/Date Received 2020-1 2-2 1
F03G 7/08 - Mécanismes produisant une puissance mécanique, non prévus ailleurs ou utilisant une source d'énergie non prévue ailleurs récupérant l'énergie produite par le balancement, le roulement, le tangage ou des mouvements semblabes, p.ex. par les vibrations d'une machine
64.
CONDUCTIVE INK WITH ENHANCED MECHANICAL FATIGUE RESISTANCE
ABSTRACT A conductive ink may comprise a high temperature thermoplastic polyurethane (TPU) and a plurality of conductive particles disposed in the high temperature TPU. The plurality of conductive particles may comprise between 60% and 95% of the conductive ink by weight. The high temperature TPU may include a melting point between 120 C and 200 C. The conductive ink may be used for external heated composite structures, such as rotor blades, fixed wings, faring, engine lip electrothermal ice protection, or the like. The conductive ink may have enhanced mechanical fatigue resistance. 18 Date Recue/Date Received 2020-11-27
B82Y 30/00 - Nanotechnologie pour matériaux ou science des surfaces, p.ex. nanocomposites
H05B 3/12 - Eléments chauffants caractérisés par la composition ou la nature des matériaux ou par la disposition du conducteur caractérisés par la composition ou la nature du matériau conducteur
ABSTRACT An ice protection system may include a rotary blade, an electrothermal heater, and a low ice adhesion surface. The low ice adhesion surface may include an adhesion strength below 100 kPa. The rotary blade may be disposed between the electrothermal heater and the low ice adhesion surface. The electrothermal heater may be disposed between the low ice adhesion surface and the rotary blade. The low ice adhesion surface may include a coating or a surface treatment. 16 Date Recue/Date Received 2020-10-30
ABSTRACT A system for use with a landing gear of an aircraft includes a drag brace assembly having an upper end configured to be rotatably coupled to the aircraft and a lower end configured to be rotatably coupled to a shock strut of the landing gear. The system further includes a jury linkage having a brace portion configured to be pivotally coupled to the drag brace assembly and a strut portion pivotally coupled to the brace portion and configured to be rotatably coupled to the shock strut. 19 Date Recue/Date Received 2020-10-30
AB STRACT A lock system for a landing gear assembly may comprise a housing and a hook configured to rotate relative to the housing. A lock pin may be configured to translate into a rotational path of the hook. An electromechanical actuator may be configured to translate the lock pin. 37 CA 3065253 2019-12-13
A nose landing gear system is disclosed. In various embodiments, the nose landing gear system includes an electro-hydraulic actuator configured to raise and lower a nose shock strut assembly; a first electro-mechanical actuator configured to steer the nose shock strut assembly; and a second electro-mechanical actuator configured to open and close a fairing door.
A method of manufacturing a cured vessel is disclosed herein. The method comprises wrapping a first bladder in a first composite laminate, wrapping a second bladder in a second composite laminate. The method further comprises joining the first composite laminate and the second composite laminate by wrapping them both in a third composite laminate to form an uncured vessel. The un-cured vessel is cured by heating the uncured vessel and pressurizing the bladder while the uncured vessel is in a vessel mold.
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 noyau; Façonnage par pistolage, c.à d. pulvérisation de fibres sur un moule, un gabarit ou un noyau
B65D 1/40 - Réceptacles rigides ou semi-rigides ayant des corps d'une seule pièce formés, p.ex. par coulage d'un matériau en métal, par moulage d'un matériau plastique, par soufflage d'un matériau vitreux, par coulage d'un matériau en céramique, par moulage d'un - Détails des parois
A system for shrinking landing gear includes a shock strut having a cylinder and a piston to be received by the cylinder. The system further includes a collar coupled to a brace linkage and the piston, a torque arm configured to resist rotation between the collar and the piston, and a shrink linkage coupled between the torque arm and the cylinder. The collar rotates relative to the cylinder in response to retraction of the landing gear. Rotation of the collar rotates the piston and the torque arm relative to the cylinder. The rotation of the collar relative to the cylinder forces, via the shrink linkage, the piston towards the aircraft attachment within the cylinder.
An apparatus for forming a composite shaft may comprise an axial fiber strip dispensing assembly and a hoop fiber strip dispensing assembly. The axial fiber strip dispensing assembly may include a plurality of fiber strip guides located circumferentially about a center axis. The plurality of fiber strip guides may be configured to dispense a plurality of circumferentially adjacent first fiber strips with the plurality of circumferentially adjacent first fiber strips extending in a generally axial direction. The hoop fiber strip dispensing assembly may be configured to dispense a second fiber strip circumferentially about the center axis.
B29C 70/24 - 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 au moins trois directions formant une structure tridimensionnelle
An auxiliary brake assembly for use in a hoist, is disclosed. The auxiliary brake assembly comprises a pinion, a fastener, and a clutch assembly. The pinion may comprise a mesh gear disposed proximate a respective mesh gear of a rotor gear. The clutch assembly may be disposed between the fastener and the mesh gear. The fastener may be configured to compress the clutch assembly in the event a cable drum of the hoist is free spinning. The compression of the clutch may lock the pinion and the rotor gear and stop the cable drum from spinning freely.
B66D 5/14 - Freins de grues, d'ascenseurs, de palans ou de treuils opérant sur des tambours, des cylindres ou des cordes avec effet axial comportant des disques
B64D 1/00 - Largage, éjection ou réception, en cours de vol, d'objets, de liquides ou similaires
B64D 9/00 - Appareillage pour manutention du fret; Appareillage pour faciliter l'embarquement des passagers ou autres
B66D 1/60 - Mécanismes d'enroulement des cordes, câbles ou chaînes; Cabestans adaptés à des usages particuliers
B66D 5/30 - Dispositifs de fonctionnement électriques
A nut locking assembly may comprise a pin, a nut, and a lock ring. The pin may include an outer diameter threaded surface and a plurality of radially inward extending grooves formed between the outer diameter threaded surface and an end of the pin. The nut may include an inner diameter threaded surface and a plurality of radially outward extending grooves formed between the inner diameter threaded surface and an axial end of the nut. The lock ring may include a plurality of outer diameter protrusions and a plurality of inner diameter protrusions.
F16B 39/10 - Blocage des vis, boulons ou écrous dans lequel le verrouillage s'effectue après vissage par une plaque ou un anneau immobile par rapport au boulon ou à l'objet
An electrical harness includes an electrical cable, an inner tubing, an outer tubing, and a braid tubing disposed between the inner tubing and the outer tubing. The braid tubing is physically contacting the inner tubing and the outer tubing to react against twisting of the electrical harness.
A tube arrangement includes a composite tube defining a centerline axis, wherein the composite tube comprises a proximal surface and a distal surface, and an end fitting comprising a first end disposed within the composite tube and a second end extending from the composite tube, wherein an outer surface of the end fitting defines a flared portion defining a terminus of the first end, a lobe portion disposed axially from the flared portion, and a terminating portion disposed axially from the lobe portion, the proximal surface conforms to a geometry of the outer surface of the end fitting, the lobe portion and the flared portion mechanically lock the end fitting to the composite tube to mitigate movement of the end fitting relative to the composite tube.
F16B 4/00 - Assemblage par retrait, p.ex. en portant les pièces à assembler à des températures différentes; Montage à force; Attaches à serrage par friction non largables
F16C 7/02 - Structure des bielles de longueur fixe
Systems and methods for operating a potable water system in an aircraft are provided. Aspects include determining, by a controller, flight data associated with a flight for the aircraft, determining passenger data associated with the flight, determining an estimated water consumption for the potable water system associated with the aircraft based on the passenger data, determining a water quantity value for the flight based at least in part on the flight data and the estimated water consumption, and transmitting, by the controller, a request for the water quantity value for the potable water system for the flight to a water fulfillment system.
A clutch having two stages for applying varied torque between an input shaft and an output shaft includes a clutchpack having input friction plates and output friction plates. The clutch further includes a first spring configured to apply a first pressure to the clutchpack to compress the clutchpack. The clutch further includes a second spring configured to apply a second pressure to the clutchpack to compress the clutchpack. The clutch further includes an engagement nut configured to move in response to rotation of the output shaft relative to the input shaft to compress the second spring in order to increase an amount of the second pressure applied to the clutchpack.
B66D 1/58 - Mécanismes de sécurité sensibles à un excès de charge
B64D 1/00 - Largage, éjection ou réception, en cours de vol, d'objets, de liquides ou similaires
B66D 1/14 - Transmission de la puissance entre sources de puissance et tambours ou cylindres
B66D 1/60 - Mécanismes d'enroulement des cordes, câbles ou chaînes; Cabestans adaptés à des usages particuliers
F16D 13/56 - Embrayages à lamelles multiples avec moyens pour augmenter la force effective entre le manchon d'actionnement ou l'organe équivalent et l'organe de pression dans lesquels la pression d'embrayage est produite uniquement par des ressorts
79.
DUAL BUS AND HARDWARE ARCHITECTURE FOR HIGH RELIABILITY CONTROL OF HELICOPTER HOIST
A control system for a component of a rescue hoist attached to an aircraft is disclosed. In various embodiments, the control system includes a first bus extending between a control module of the rescue hoist and a control input device; a second bus extending between the control module of the rescue hoist and the control input device; and a hardwire extending between the control module of the rescue hoist and the control input device.
A control system for a rescue hoist attached to an aircraft is disclosed. In various embodiments, the control system includes a first bus extending between a control module of the rescue hoist and a control input device; and a second bus extending between the control module of the rescue hoist and the control input device. The first bus is configured to transmit a first signal from the control input device to the control module and the second bus is configured to transmit a second signal from the control input device to the control module, both the first signal and the second signal being generated by the control input device in response to a manipulation of the control input device.
A system for shrinking landing gear includes a shock strut having a cylinder and a piston to be received by the cylinder. The system further includes an upper cam fastened to the piston and a lower cam fastened to the cylinder. The system further includes a brace configured to be coupled to the shock strut to lock the landing gear in a deployed position, and to fold towards the shock strut during retraction of the landing gear. The system further includes a collar coupled to the brace and the piston and configured to rotate relative to the cylinder in response to folding of the brace such that rotation of the collar rotates the piston and the upper cam relative to the lower cam, the rotation of the upper cam relative to the lower cam forcing the piston towards the aircraft attachment within the cylinder.
A bracket manifold for a landing gear assembly is disclosed. In various embodiments, the bracket manifold includes a mounting plate having a central portion and a first wing portion extending from the central portion; and a first manifold section integrated monolithically into at least one of the central portion and the first wing portion of the mounting plate.
F16L 3/01 - Supports pour tuyaux, pour câbles ou pour conduits de protection, p.ex. potences, pattes de fixation, attaches, brides, colliers pour supporter ou guider les tuyaux, les câbles ou les conduits de protection entre des points mobiles les uns par rapport aux autres, p.ex. canaux mobiles
A veneer panel includes a face layer formed from a carbon fiber sheet. The veneer panel further includes a backing layer. The veneer panel further includes a thermoset dry film adhesive located between the face layer and the backing layer and attaching the face layer to the backing layer.
B32B 7/12 - Liaison entre couches utilisant des adhésifs interposés ou des matériaux interposés ayant des propriétés adhésives
B32B 9/00 - Produits stratifiés composés essentiellement d'une substance particulière non couverte par les groupes
B32B 21/14 - Produits stratifiés composés essentiellement de bois, p.ex. une planche de bois, une feuille de placage, une feuille de bois aggloméré comprenant une planche de bois ou une feuille de bois de placage
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
84.
EDGE DAMAGE TOLERANT HEATED AND UNHEATED COMPOSITE PANELS WITH ROTATED HONEYCOMB EDGE PIECES
A panel assembly for use in an aircraft includes a surface. The panel assembly further includes a body portion including a honeycomb material having multiple body volumes oriented perpendicular to the surface. The panel assembly further includes an edge portion extending around an edge of the panel assembly and including the honeycomb material having multiple edge volumes oriented parallel to the surface in order to increase edge strength of the panel assembly.
B32B 3/02 - Caractérisés par des caractéristiques de forme en des endroits déterminés, p.ex. au voisinage des bords
A47B 96/20 - Panneaux de meubles ou éléments de meubles similaires
B32B 3/12 - Produits stratifiés caractérisés essentiellement par le fait qu'une des couches comporte des discontinuités ou des rugosités externes ou internes, ou bien qu'une des couches est de forme générale non plane; Produits stratifiés caractérisés essentiellement par des particularismes de forme caractérisés par une couche discontinue, c. à d. soit continue et percée de trous, soit réellement constituée d'éléments individuels caractérisés par une couche d'alvéoles disposées régulièrement, soit formant corps unique dans un tout, soit structurées individuellement ou par assemblage de bandes indépendantes, p.ex. structures en nids d'abeilles
B64D 11/00 - Arrangements pour passagers ou équipage; Installations de postes de pilotage non prévues ailleurs
85.
BONDED STRUCTURAL RIB FOR HEATED AIRCRAFT LEADING EDGE
An aircraft may include a fuselage and a wing extending away from the fuselage to a wing tip. The wing may have a leading edge portion, a suction side portion, and a pressure side portion. A thermoelectric element may be coupled to an inner surface of the wing. A chemical adhesive may be disposed on a thermoelectric inner surface. A structural rib may be adhesively bonded to the thermoelectric element by curing the chemical adhesive. The structural rib may be mechanically fastened to a suction side of the wing and to a pressure side of the wing.
Disclosed is a sensor system for retrofitting a water supply of an airplane to detect leakage. The system includes a housing having a first band with an inner diameter sized to receive a necked portion of a valve for consumer access to the water supply. The system includes a first transducer disposed on the first band operable to provide a position measurement corresponding to a relative position between a head of the valve and the necked portion. The system includes a second transducer operable to provide a pressure measurement corresponding to a pressure of a compressed gas in a water tank of the water supply. The system includes a controller having input channels operable to receive the position measurement and the pressure measurement. The controller is operable to indicate a leak condition.
G01M 3/26 - Examen de l'étanchéité des structures ou ouvrages vis-à-vis d'un fluide par utilisation d'un fluide ou en faisant le vide par mesure du taux de perte ou de gain d'un fluide, p.ex. avec des dispositifs réagissant à la pression, avec des indicateurs de débit
B64F 5/60 - Test ou inspection des composants ou des systèmes d'aéronefs
A method for monitoring a dual-stage shock strut may include measuring a first primary chamber pressure when the dual-stage shock strut is in a first state, measuring a first secondary chamber pressure when the dual-stage shock strut is in the first state, measuring a shock strut stroke when the dual-stage shock strut is in the first state, measuring a first temperature, measuring a second temperature, measuring a second primary chamber pressure when the dual-stage shock strut is in a second state, measuring a second secondary chamber pressure when the dual-stage shock strut is in the second state, and determining a servicing condition of the shock strut based upon at least the first primary chamber pressure, the first secondary chamber pressure, the shock strut stroke, the first temperature, the second temperature, the second primary chamber pressure, and the second secondary chamber pressure.
F16F 9/06 - Ressorts, amortisseurs de vibrations, amortisseurs de chocs ou amortisseurs de mouvement de structure similaire, utilisant un fluide ou moyen équivalent comme agent d'amortissement utilisant à la fois un gaz et un liquide
F16F 9/32 - Ressorts, amortisseurs de vibrations, amortisseurs de chocs ou amortisseurs de mouvement de structure similaire, utilisant un fluide ou moyen équivalent comme agent d'amortissement - Parties constitutives
A cable rotation blocking system (CRBS) (300) is described herein. The CRBS extends along an axis X between a first end (305) and a second end (303), and comprises a first section provided at the first end (305), the first section being configured to be connectable to a cable (100). The CRBS further comprises a second section provided at the second end (303), the second section being configured to be attachable to a load. With the CRBS described herein, when no load, or a load up to an upper load threshold is attached to the second section, the second section is rotatable about the axis X, relative to the first section, however, when a load higher than the upper load threshold is attached to the second section, the second section is prevented from rotation about the axis relative to the first section.
A self-adjusting automatic load brake for a hoist is disclosed. In various embodiments, the load brake includes a first shaft defining an annular hollow portion; a second shaft defining an engagement portion, the engagement portion configured for sliding disposition within the annular hollow portion; a first reaction plate coupled to the first shaft; a second reaction plate coupled to the second shaft; and a plurality of friction discs, with at least one of the plurality of friction discs coupled to a cup and disposed between the first reaction plate and the second reaction plate, the annular hollow portion of the first shaft and the engagement portion of the second shaft being sized and configured to accommodate thinning of the plurality of friction discs.
B66D 5/14 - Freins de grues, d'ascenseurs, de palans ou de treuils opérant sur des tambours, des cylindres ou des cordes avec effet axial comportant des disques
A62B 1/10 - Dispositifs pour faire descendre des personnes hors des bâtiments ou dans des situations analogues à l'aide de dispositifs de descente à câble avec mécanisme de freinage pour treuils ou poulies à action mécanique
B64D 1/00 - Largage, éjection ou réception, en cours de vol, d'objets, de liquides ou similaires
B66D 1/60 - Mécanismes d'enroulement des cordes, câbles ou chaînes; Cabestans adaptés à des usages particuliers
F16D 65/52 - Dispositifs de réglage mécaniques agissant automatiquement dans une direction pour le réglage d'un jeu excessif
90.
AUTOMATIC LOAD BRAKE HAVING WEAR-INDUCED LOCKING MECHANISM
An automatic load brake having a wear-induced locking mechanism for a hoist is disclosed. In various embodiments, the load brake includes a first shaft defining an annular hollow portion and a radially outer surface; a second shaft defining an engagement portion and a radially inner surface, the radially inner surface configured to engage the radially outer surface; a first reaction plate coupled to the first shaft; a second reaction plate coupled to the second shaft; and a plurality of friction discs, with at least one of the plurality of friction discs coupled to a cup and disposed between the first reaction plate and the second reaction plate, the annular hollow portion of the first shaft being configured to lock to the engagement portion of the second shaft upon thinning of the plurality of friction discs.
B66D 5/14 - Freins de grues, d'ascenseurs, de palans ou de treuils opérant sur des tambours, des cylindres ou des cordes avec effet axial comportant des disques
A62B 1/10 - Dispositifs pour faire descendre des personnes hors des bâtiments ou dans des situations analogues à l'aide de dispositifs de descente à câble avec mécanisme de freinage pour treuils ou poulies à action mécanique
B64D 1/00 - Largage, éjection ou réception, en cours de vol, d'objets, de liquides ou similaires
B66D 1/60 - Mécanismes d'enroulement des cordes, câbles ou chaînes; Cabestans adaptés à des usages particuliers
F16D 65/52 - Dispositifs de réglage mécaniques agissant automatiquement dans une direction pour le réglage d'un jeu excessif
A clutch assembly for a hoist may comprise a first epicyclic gear train and a first set of friction disks rotationally coupled to the first epicyclic gear train. A second set of friction disks may be in operable communication with the first set of friction disks. Torque may be transferred between the first set of friction disks and the second set of friction disks by means of a friction coupling between the first set of friction disks and the second set of friction disks. A pinion may be rotationally coupled to the second set of friction disks. A splined portion of the pinion may form an output of the clutch assembly.
B66D 1/22 - Mécanismes différentiels ou à planétaires
B64D 1/00 - Largage, éjection ou réception, en cours de vol, d'objets, de liquides ou similaires
B66D 1/58 - Mécanismes de sécurité sensibles à un excès de charge
F16D 13/76 - Embrayages à friction spécialement adaptés pour leur incorporation dans d'autres pièces de transmission, c. à d. une des pièces au moins de l'embrayage ayant également une autre fonction, p.ex. étant le disque d'une poulie
An armrest for a seat may comprise paneling and an easy hook assembly. The easy hook assembly may include a flange and a keyhole protrusion. The flange and the keyhole protrusion may each extending beyond an exterior surface of the paneling. The flange and the keyhole protrusion may allow the armrest to be installed after the paneling is attached.
A method for monitoring a shock strut may comprise measuring a first shock strut pressure, measuring an ambient temperature, measuring a shock strut stroke, measuring a second shock strut pressure, and determining a servicing condition of the shock strut based upon the first shock strut pressure, the ambient temperature, the shock strut stroke, and the second shock strut pressure, wherein the servicing condition indicates whether it is desirable for the shock strut to be serviced with at least one of a liquid and a gas. The first shock strut pressure and the shock strut stroke may be measured before the takeoff event with a weight of an aircraft supported by the shock strut.
F16F 9/06 - Ressorts, amortisseurs de vibrations, amortisseurs de chocs ou amortisseurs de mouvement de structure similaire, utilisant un fluide ou moyen équivalent comme agent d'amortissement utilisant à la fois un gaz et un liquide
F16F 9/32 - Ressorts, amortisseurs de vibrations, amortisseurs de chocs ou amortisseurs de mouvement de structure similaire, utilisant un fluide ou moyen équivalent comme agent d'amortissement - Parties constitutives
A vehicle including a housing, and a vehicle seat disposed in the housing. The vehicle further includes at least one radial slit disc energy attenuation assembly having an upper end coupled to the vehicle seat and a lower end coupled the housing. The radial slit disc energy attenuation assembly includes a slit disc stack having a plurality of deflectable discs configured to deflect in response to realizing a force applied by the vehicle seat.
B60N 2/42 - Sièges spécialement adaptés aux véhicules; Agencement ou montage des sièges dans les véhicules à des fins particulières ou pour des véhicules particuliers le siège étant construit pour protéger son occupant des effets des forces d'accélération anormales, p.ex. sièges anticollision ou sièges de sécurité
B60N 2/427 - Sièges spécialement adaptés aux véhicules; Agencement ou montage des sièges dans les véhicules à des fins particulières ou pour des véhicules particuliers le siège étant construit pour protéger son occupant des effets des forces d'accélération anormales, p.ex. sièges anticollision ou sièges de sécurité - le siège ou ses parties constitutives se déplaçant lors d'une collision
B64D 11/06 - Aménagements ou adaptations des sièges
F16F 7/00 - Amortisseurs de vibrations; Amortisseurs de chocs
F16F 7/08 - Amortisseurs de vibrations; Amortisseurs de chocs avec surfaces de friction à déplacement rectiligne l'une le long de l'autre
A method of making a multi-section tank with composite material includes pre- tensioning the composite material, wrapping a soluble tool in the composite material, and curing the composite material around the soluble tool. The composite material is pre- tensioned with force to align fibers in the composite material.
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 noyau; Façonnage par pistolage, c.à d. pulvérisation de fibres sur un moule, un gabarit ou un noyau
B29C 33/52 - Moules ou noyaux; Leurs détails ou accessoires comportant des moyens ou conçus spécialement pour faciliter le démoulage d'objets, p.ex. des objets à contre-dépouille solubles ou fusibles
B29C 70/40 - Façonnage ou imprégnation par compression
A method of making a blind hole in a wall of a multi-section tank during manufacture includes inserting a thin, flexible composite spacer ring in a hole in a composite material between mating parts of a soluble tool. The composite spacer ring is cured to the composite material during curing and maintains the hole between sections of the tank once completed.
Provided are embodiments for a system and method for performing real-time performance and health monitoring of an ice detector system. Embodiments include sensing, by a current sensor, a current parameter of a drive coil of an ice detector circuit, and monitoring a performance and health of the ice detector circuit based at least in part on the current parameter, where the drive coil is coupled to a feedback coil that is configured to provide a feedback signal to a driver circuit to control the drive coil. Embodiments also include comparing the performance of the ice detector circuit and expected performance of the ice detector circuit, and providing a report based at least in part on the comparison.
Disclosed is a multilayer structure, comprising: a first heater layer comprising a CNT heater, wherein the CNT heater comprises a composite of carbon nanotubes and silicone; and a second heater layer comprising a PTC heater, wherein the PTC heater comprises a composite of carbon black and polymer; wherein the first heater layer and the second heater layer are first and second respectively in an electrical series; wherein the first heater layer has a negative temperature coefficient with respect to electrical resistivity; and wherein the second heater layer has a positive temperature coefficient with respect to electrical resistivity. Also disclosed is an aircraft component comprising the multilayer structure.
H05B 3/12 - Eléments chauffants caractérisés par la composition ou la nature des matériaux ou par la disposition du conducteur caractérisés par la composition ou la nature du matériau conducteur
B82Y 30/00 - Nanotechnologie pour matériaux ou science des surfaces, p.ex. nanocomposites
B32B 7/025 - Propriétés électriques ou magnétiques
B32B 27/04 - Produits stratifiés composés essentiellement de résine synthétique comme substance d'imprégnation, de collage, ou d'enrobage
99.
COMPOSITE POTABLE WATER TANK AND METHOD OF FORMING
A water tank includes a compression molded tank shell. The tank shell includes a back panel and a side panel extending from the back panel. The side panel defines an outer perimeter of the water tank. A compression molded front panel is secured to the side panel to enclose an interior of the water tank. A method of forming a potable water tank includes forming a tank shell via a compression molding process, the tank shell including a back panel and a side panel extending from the back panel, the side panel defining an outer perimeter of the water tank. A front panel is separately formed by compression molding, and the front panel is secured to the side panel thereby enclosing an interior of the water tank.
B65D 1/00 - Réceptacles rigides ou semi-rigides ayant des corps d'une seule pièce formés, p.ex. par coulage d'un matériau en métal, par moulage d'un matériau plastique, par soufflage d'un matériau vitreux, par coulage d'un matériau en céramique, par moulage d'un
B29C 39/02 - Moulage par coulée, c. à d. en introduisant la matière à mouler dans un moule ou entre des surfaces enveloppantes sans pression significative de moulage; Appareils à cet effet pour la fabrication d'objets de longueur définie, c. à d. d'objets séparés
B65D 1/42 - Pièces ou éléments de renfort ou de consolidation
A clutch assembly includes a first gear, a second gear, a first proximity sensor configured to determine a first number of teeth of the first gear that pass by the first proximity sensor within a period of time, and a second proximity sensor configured to determine a second number of teeth of the second gear that pass by the second proximity sensor within the period of time.
brevets
