A landing gear system for a vehicle includes a landing gear configured for reciprocating motion between a stowed position and a deployed position. The landing gear has a linkage with a first link rotatably coupled to a second link. The linkage reciprocates between folded and extended states when the landing gear reciprocates between the stowed and deployed positions, respectively. A fail-secure downlock includes first and second electromagnets fixedly positioned relative to the first and second links, respectively. The first electromagnet is proximate to the second electromagnet when the landing gear is in the stowed position. The first electromagnet is attracted to the second electromagnet when the downlock is in the locked state. The first electromagnet is repelled by the second electromagnet when the downlock is in the unlocked state.
A landing gear system includes a landing gear assembly coupled to a body of a vehicle and configured for reciprocating motion between a retracted position and an extended position. A fail-secure uplock assembly is reciprocal between a locked state and an unlocked state. A first electromagnet and a first permanent magnet are mounted to the body, and a second electromagnet and a second permanent magnet are mounted to a component of the landing gear assembly. The first and second electromagnets generate magnetic fields with reversible polarities. When the landing gear assembly is in the retracted position, the first permanent magnet is attracted to the second permanent magnet. The first electromagnet is attracted to the second electromagnet when the uplock assembly is in the locked state and is repelled by the second electromagnet when the uplock assembly is in the unlocked state.
A shock absorber for a vehicle includes a cylinder and a piston, a portion of which slidably disposed with the cylinder. A magnetic target is fixedly positioned relative to the piston, and a sensor is fixedly positioned relative to the cylinder. The sensor generates a signal according to the position of the magnet target relative to the sensor.
B64C 25/58 - Aménagements ou adaptations des amortisseurs ou des ressorts
G01L 5/00 - Appareils ou procédés pour la mesure des forces, du travail, de la puissance mécanique ou du couple, spécialement adaptés à des fins spécifiques
An aircraft braking system including a braking actuator; a primary hydraulic fluid supply circuit configured to supply pressurised hydraulic fluid to the braking actuator; and a secondary hydraulic fluid supply circuit including a piezoelectric pump configured to supply pressurised hydraulic fluid to the braking actuator.
A main fitting includes an elongate piston and a cylinder configured to slidingly receive the piston. A first end of the piston extends from a first end of the cylinder, and a second end of the piston extends from a second end of the cylinder. The first end of the cylinder comprises a bearing surface engaging the piston to limit translation of the piston relative to the cylinder to a longitudinal direction.
A landing gear assembly for a vehicle, such as a helicopter, includes a linkage coupled to the vehicle and configured to reciprocate between a stowed position and a deployed position. A shock strut forms a part of the linkage. The landing gear assembly further includes a side brace having a first end coupled to the linkage and a second end coupled to the vehicle. The side brace provides a driving force that reciprocates the linkage between the stowed and deployed position. The side brace includes an energy attenuation system that dissipates energy when a compressive load on the side brace exceeds a predetermined threshold.
B64C 25/26 - Systèmes de commande ou de verrouillage à cet effet
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
B64C 25/58 - Aménagements ou adaptations des amortisseurs ou des ressorts
A pin for a pinned joint includes a hollow body with a first and second end caps coupled to first and second ends, respectively. The body and the end caps at least partially define a cavity within the body, wherein at least one aperture extends through the hollow body. A main piston is slidably disposed within the cavity and divides the cavity into a first chamber proximate to the first end and a second chamber proximate to the second end and fluidly isolated from an environment around the body. A lubricant is disposed within the first chamber. The main piston moves toward the first end of the body when a pressure in the second chamber is greater than a pressure of the environment. Movement of the main piston toward the first end of the body discharges lubricant through the at least one aperture.
A fuse pin valve includes a housing, a piston, and a mechanical fuse, such as a fuse pin. As assembled, the piston is movably disposed in the housing and is retained in a static position by the fuse pin. Upon a certain pressure (e.g., an abnormal pressure) acting on the piston, the fuse pin fails, thereby releasing the piston to move from a first or start position to second or end position. In the start position of the piston, the valve is in a first operational state (e.g., a closed state). In the end position of the piston, the valve is in a second operational state (e.g., an open state, fully open states, etc.). In other embodiments, in the start position of the piston the valve is in an open state, and in the end position of the piston the valve is in a closed state.
A load detection system detects loads applied to a landing gear assembly during landing. The landing gear assembly includes an axle coupled to a piston rod of a compressible shock strut and a wheel rotatably mounted the axle. A torque link includes a lower link coupled to the piston rod of the shock strut so that compression of the shock strut rotates the link about a first axis. The load detection system includes a probe rotatably coupled about a second axis. The probe engages a ground surface when the shock strut is uncompressed and the wheel contacts the ground surface. The lower link rotates the probe as the shock strut compresses. A sensor senses a position of the probe, which corresponds to a load on the wheel when the shock strut is uncompressed and the wheel is in contact with the ground surface.
B64C 25/32 - Trains d'atterrissage caractérisés par les éléments de contact avec le sol ou une surface analogue
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
B64C 25/58 - Aménagements ou adaptations des amortisseurs ou des ressorts
B64D 45/00 - Indicateurs ou dispositifs de protection d'aéronefs, non prévus ailleurs
G01L 5/00 - Appareils ou procédés pour la mesure des forces, du travail, de la puissance mécanique ou du couple, spécialement adaptés à des fins spécifiques
A motor is configured to apply a rotational force to a wheel that includes a rim rotatably mounted to an axle about a first axis. The motor has a rotor coupled to the rim. The rotor has an interior cavity and a plurality of radial slots formed therein. A cylindrical stator is disposed within the cavity and has a second axis offset from the first axis. The stator is fixed in rotation relative to the axle. The motor further includes a plurality of vanes, each vane being slidably disposed within one of the plurality of radial slots. A compressed gas source is in fluid communication with the cavity and selectively provides compressed gas to the cavity to rotate the rotor.
F01C 1/356 - "Machines" ou machines motrices à piston rotatif ayant des caractéristiques couvertes par au moins deux des groupes , , , ou par l'un de ces groupes associées à un autre type de mouvement entre les organes coopérants ayant à la fois le mouvement défini dans le groupe ou et un mouvement alternatif entre les organes coopérants comportant des organes obturateurs se déplaçant par rapport à l'organe externe
B64C 25/32 - Trains d'atterrissage caractérisés par les éléments de contact avec le sol ou une surface analogue
11.
Coupled gas springs on adjacent gears for the avoidance of failure case loads
A shock absorber system for a vehicle includes a first shock absorber with a first cavity and a second shock absorber with a second cavity, wherein the first and second shock absorbers are located on a same side of the vehicle. The shock absorber system further includes a conduit in fluid communication with the first and second shock absorbers so that the second cavity maintains fluid communication with the first cavity through the conduit. The first and second cavities are at least partially filled with a gas.
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
A drive augmenter provide supplemental drive power to the wheel of a landing gear with a drive system. The landing gear has a wheel rotatably mounted to an axle, and the drive system selectively provides a driving force to rotate the wheel. The drive augmenter includes a piston slidably disposed with a cylinder, and selective pressurization of the cylinder drives reciprocating translation of the piston within the cylinder. A crank is coupled to the piston by a rod and is also coupled to a crankshaft. The crank is configured to convert translation of the piston into rotation of the crankshaft. The drive augmenter further includes a drive shaft coupled to the wheel and a clutch configured to selectively transfer rotation of the crankshaft to the drive shaft.
A maglev system includes a maglev vehicle that reciprocates between a levitated state and a non-levitated state. The vehicle includes a capsule supported by a first left wheel and a corresponding first right wheel when the vehicle is in the non-levitated state. The system further includes a track having a left rail and a right rail, each of the left and right rails having a plurality of plates arranged in series. Proximate ends of adjacent plates define a joint. Each rail provides a support surface that the first left and right wheels rollingly engage when the vehicle is in the non-levitated state. The joints of the left rail are offset in a longitudinal direction from the joints of the right rail.
An aircraft has retractable landing gear configured to reciprocate between a deployed position and a stowed position. A landing gear door installation includes a first door rotatably coupled to the aircraft about a first axis for movement between a raided position and lowered position. The door installation further includes a second door located aft of the first door and coupled to the aircraft for movement between a first position when the landing gear is in the stowed position, and a second position when the landing gear is in the deployed position. A portion of the first door overlaps a portion of the second door when the first door is in the raised position and the second door is in the first position so that the first door blocks deployment of the second door to the second position.
A feedback system senses a steering position of a nose wheel assembly for an aircraft. The nose wheel assembly has a first element rotatably associated with a second element about an axis, and the rotational position of the first element relative to the second element corresponds to the steering position of the nose wheel assembly. The feedback system includes a first magnetic field sensor fixedly positioned relative to the first element and configured to sense a first element orientation. A second magnetic field sensor is fixedly positioned relative to the second element and configured to sense a second element orientation. The feedback system further includes a controller programmed to determine the steering position of the nose wheel according to the sensed first element orientation and the sensed second element orientation.
B64C 25/50 - Atterrisseurs orientables; Amortissement du shimmy
B62D 6/00 - Dispositions pour la commande automatique de la direction en fonction des conditions de conduite, qui sont détectées et pour lesquelles une réaction est appliquée, p.ex. circuits de commande
16.
PASSIVE EDDY-CURRENT WHEEL BRAKE WITH CONICAL FORM
A brake assembly is suitable for use in conjunction with a wheel having a rim rotatably mounted to an axle. The brake assembly includes a rotor configured to rotate about the axis with the rim. The rotor has a first frustoconical rotor surface and either a conductive element or a magnet. The brake assembly further includes a stator fixed in rotation about the axis and configured for selective translation parallel to the axis. The stator has a first frustoconical stator surface proximate to the first frustoconical rotor surface and a conductive element, when the stator has a magnet, or a magnet, when the stator has a conductive element.
H02K 49/04 - Embrayages dynamo-électriques; Freins dynamo-électriques du type à induction asynchrone du type à courants de Foucault ou à hystérésis
F16D 65/18 - Mécanismes d'actionnement pour freins; Moyens pour amorcer l'opération de freinage à une position prédéterminée disposés dans, ou sur le frein adaptés pour rapprocher les organes par traction
17.
Backlash measurement system for an electromechanical actuator
A drive system includes a motor having a rotatable output shaft that is operably coupled to a lead screw by a transmission that converts rotary output of the motor into linear translation of the lead screw. The drive system further includes a position sensor configured to sense a position of the lead screw. A method for determining a backlash of the drive system includes the steps of sensing an initial position and driving the lead screw in a first direction to a calculated second position by controlling the motor to rotate the output shaft an amount that corresponds to a distance between the initial position and the calculated second position. The method further includes the steps of sensing an actual second position of the lead screw; and determining a backlash value according to a difference between the calculated second position and the actual second position.
A brake assembly is suitable for use with a vehicle wheel that has a rim rotatably mounted to an axle. The brake assembly includes a housing fixedly positioned relative to the axle and a plurality of disks disposed within the housing and fixedly positioned relative to the rim. A fluid is disposed within the housing and has a selectively variable viscosity. The viscosity of the fluid is selectively increased to increase a braking force applied to the wheel.
F16D 27/115 - Embrayages actionnés magnétiquement; Leur commande ou leurs circuits électriques avec un électro-aimant ne tournant pas avec un organe de l'embrayage, c. à d. sans bagues collectrices avec des organes d'embrayage mobiles selon l'axe avec des surfaces de friction plates, p.ex. des disques à plus de deux disques, p.ex. à lamelles multiples
F16D 55/00 - Freins à surfaces de freinage substantiellement radiales pressées l'une contre l'autre dans une direction axiale, p.ex. freins à disques
F16D 55/32 - Freins à un seul disque tournant actionnés par un dispositif à pression de fluide disposé dans, ou sur le frein
F16D 55/40 - Freins à plusieurs disques tournants disposés tous côte à côte actionnés par un dispositif à pression de fluide disposé dans, ou sur le frein
An aircraft landing gear assembly having a first landing gear element movably coupled relative to a second landing gear element to move between a first condition and a second condition. The aircraft landing gear assembly further comprises a fibre composite leaf spring formed from a plurality of composite layers and arranged between the first and second elements, the leaf spring being arranged to bend when the first element moves from the first condition to the second condition. The fibre composite leaf spring comprises a first region and a second region, wherein the number of composite layers in the first region is greater than the number of composite layers in the second region. The landing gear further comprises a mounting assembly arranged to engage the first region of the leaf spring to couple the leaf spring to the first landing gear element.
B32B 5/02 - Produits stratifiés caractérisés par l'hétérogénéité ou la structure physique d'une des couches caractérisés par les caractéristiques de structure d'une couche comprenant des fibres ou des filaments
B32B 5/26 - Produits stratifiés caractérisés par l'hétérogénéité ou la structure physique d'une des couches caractérisés par la présence de plusieurs couches qui comportent des fibres, filaments, grains ou poudre, ou qui sont sous forme de mousse ou essentiellement poreuses une des couches étant fibreuse ou filamenteuse un autre couche également étant fibreuse ou filamenteuse
Ce gabarit de perçage (1) pour insertion dans une pièce à percer de l'intérieur au niveau d'une protubérance externe, comprend un corps principal (5), un bras de positionnement (7) par rapport à la protubérance externe relié au corps principal (5), au moins une perceuse (8 ; 9) placée dans le corps principal (5), un circuit de commande à distance de l'au moins une perceuse (8 ; 9), un dispositif d'aspiration de copeaux placé dans le corps principal (5) et un dispositif de serrage (12) du corps principal (5) par rapport à la pièce à percer de l'intérieur.
This application relates to an aircraft braking system comprising: a braking actuator; a primary hydraulic fluid supply circuit configured to supply pressurised hydraulic fluid to the braking actuator; and a secondary hydraulic fluid supply circuit comprising a piezoelectric pump configured to supply pressurised hydraulic fluid to the braking actuator.
B60T 8/17 - Utilisation de moyens de régulation électriques ou électroniques pour la commande du freinage
B60T 13/14 - Dispositions relatives à l'alimentation en pression utilisant des accumulateurs ou des réservoirs
B60T 13/68 - Commande électrique des systèmes de freins à fluide sous pression par valves commandées électriquement
B60T 13/74 - Transmission de l'action de freinage entre l'organe d'attaque et les organes terminaux d'action, avec puissance de freinage assistée ou relais de puissance; Systèmes de freins incorporant ces moyens de transmission, p.ex. systèmes de freinage à pression d'air avec entraînement ou assistance électrique
A structural component, or parts thereof, for a machine system or vehicle, such as an aircraft, is provided. In some examples, the structural component includes at least one embedded passageway or line. In other examples, the passageway or line is formed integrally on the exterior surface of the structural component. In some of these examples, the structural component can benefit from additive manufacturing techniques or methodologies.
B60R 16/02 - Circuits électriques ou circuits de fluides spécialement adaptés aux véhicules et non prévus ailleurs; Agencement des éléments des circuits électriques ou des circuits de fluides spécialement adapté aux véhicules et non prévu ailleurs électriques
H02G 3/04 - Tubes ou conduits de protection, p.ex. échelles à câbles ou goulottes de câblage
A disclosed controller is configured with logic that, when executed, performs actions to extend landing gear of a maglev vehicle. The actions include receiving a height control target value and transitioning between a standby control state and an active control state. The controller maintains the landing gear in a fixed position when the controller is in the standby control state, and the controller controls extension and retraction of the landing gear according to the height control target value when the controller is in the active control state.
B61L 3/00 - Dispositifs le long de la voie commandant des dispositifs sur le véhicule ou sur le train, p.ex. pour relâcher les freins, pour manœuvrer un signal avertisseur
B61C 11/00 - Locomotives ou automotrices caractérisées par la manière dont l'effort de traction est appliqué; Disposition des organes de roulement autres que les roues motrices normales
B61K 13/00 - Autres dispositifs auxiliaires ou accessoires pour les chemins de fer
An aircraft landing gear assembly includes a main fitting comprising having a main barrel and a cross beam fixedly positioned relative to the main barrel and extending radially from the main barrel. The main fitting further includes a drag arm with a first end pivotally coupled to the cross beam by a first pivotal connection and a second end pivotally coupled to the main barrel by a second pivotal connection.
Wheel acceleration systems are disclosed that provide a motive force to at least one wheel of an aircraft, in order to accelerate the aircraft to takeoff speed with the assistance of main engine thrust. The wheel acceleration system includes a pyrotechnic unit configured to generate expanding gases by combusting a propellant, and a rotary propulsion unit pneumatically coupled to the pyrotechnic unit. The rotary propulsion unit includes an impeller configured to be driven by the expanding gases and to deliver torque to the wheel.
B64C 25/36 - Aménagements ou adaptations des roues, des pneumatiques ou des essieux
B60K 3/04 - Agencement ou montage des ensembles de propulsion à vapeur ou à gaz sous pression du type à turbine
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
A brake assembly is configured for use with a wheel in an ambient environment. The wheel includes a rim rotatably mounted to an axle. The brake assembly includes a brake stack and an actuation assembly configured to selectively apply a force to the brake stack. A cover sealingly engaged the rim to at least partially define a fluidic barrier between a brake cavity and the ambient environment. The brake stack is located within the brake cavity.
Wheel acceleration systems are disclosed that provide a motive force to at least one wheel of an aircraft, in order to accelerate the aircraft to takeoff speed with the assistance of main engine thrust. The wheel acceleration system includes a pyrotechnic unit configured to generate expanding gases by combusting a propellant, and a rotary propulsion unit pneumatically coupled to the pyrotechnic unit. The rotary propulsion unit includes an impeller configured to be driven by the expanding gases and to deliver torque to the wheel.
B64C 25/40 - Trains d'atterrissage caractérisés par les éléments de contact avec le sol ou une surface analogue un mouvement rotatif étant communiqué aux éléments avant l'impact
28.
SHAFT DRIVEN SELF-POWERED LANDING GEAR WITH HUBCAP MOUNTED GEAR REDUCTION
A landing gear system includes wheel rotatably coupled to an axle. A driveshaft extends through a cavity formed in the axle and is rotatable about an axis. A planetary gear includes a sun gear operably coupled to the drive shaft and a planet gear operably engaging the sun gear. The planetary gear further includes a ring gear that surrounds and is operably coupled to the planet gear so that rotation of the drive shaft rotates the ring gear. A clutch assembly is selectively moveable between an engaged state and a disengaged state. The clutch assembly transfers rotation of the ring gear to the wheel when the clutch assembly is in the engaged state, and the clutch assembly does not transfer rotation of the wheel to the ring gear when the clutch assembly is in the disengaged state.
A landing gear system includes a drive shaft extending through an axle. A wheel with a drive surface is rotatably coupled to the axle. A drive assembly, which has disengaged and engaged states, includes a drive element and an idler element. The drive element, which has an engagement feature, is coupled to the drive shaft for rotation about an axis. The engagement feature has first and second diameters when the drive assembly is in the disengaged and engaged states, respectively. The idler element is frictionally engaged with the engagement feature of the drive element to transfer rotation of the drive element to the wheel when the drive assembly is in the engaged state. The idler element is disengaged from at least one of the engagement feature of drive element and the wheel when the drive assembly is in the disengaged state.
B64C 25/40 - Trains d'atterrissage caractérisés par les éléments de contact avec le sol ou une surface analogue un mouvement rotatif étant communiqué aux éléments avant l'impact
B64C 25/36 - Aménagements ou adaptations des roues, des pneumatiques ou des essieux
A shock absorber includes a housing and an end wall slidably disposed within the housing. The end wall and the housing cooperate to define at least a portion of a cavity within the housing. The cavity is filled with a fluid, and a piston is slidably disposed within the cavity. Movement of the piston within the cavity compresses the fluid to provide a spring force. The shock absorber further includes a compensator coupled to the end wall. The compensator positions the end wall within the housing to change a volume of the cavity in response to a change in a temperature of a first element of the compensator.
F16F 5/00 - Ressorts à liquide dans lesquels le liquide travaille comme un ressort par compression, p.ex. combinés avec une action d'étranglement; Combinaisons de dispositifs comportant des ressorts à liquide
F16F 9/30 - Ressorts, amortisseurs de vibrations, amortisseurs de chocs ou amortisseurs de mouvement de structure similaire, utilisant un fluide ou moyen équivalent comme agent d'amortissement avec un matériau solide ou semi-solide, p.ex. des masses pâteuses, comme agent d'amortissement
31.
Methods for monitoring service interval of an actuator
A method of determining a service interval for an actuator of a landing gear assembly is suitable for used with a landing gear assembly in which the actuator positions the landing gear assembly between a stowed position and a deployed position. The method includes the steps of determining an actuator travel value for a time interval and increasing a total actuator accumulated travel value by the actuator travel value for the time interval. The method further includes the step of comparing the total actuator accumulated travel value to a predetermined value.
B64F 5/60 - Test ou inspection des composants ou des systèmes d'aéronefs
G01D 5/14 - Moyens mécaniques pour le transfert de la grandeur de sortie d'un organe sensible; Moyens pour convertir la grandeur de sortie d'un organe sensible en une autre variable, lorsque la forme ou la nature de l'organe sensible n'imposent pas un moyen de conversion déterminé; Transducteurs non spécialement adaptés à une variable particulière utilisant des moyens électriques ou magnétiques influençant la valeur d'un courant ou d'une tension
32.
GAS DISSOLUTION PREDICTION SYSTEM AND METHOD FOR AN AIRCRAFT SHOCK STRUT
Techniques and methodologies for servicing a shock strut are provided that account for the variability in gas solubility of the shock strut while in-service. These examples incorporates knowledge of the shock strut's stoke history in order to estimate/predict the amount of gas in solution, its percentage saturation, etc. This may permit a more refined knowledge of the true servicing state of the shock strut.
Techniques and methodologies for servicing a shock strut are provided that account for the variability in gas solubility of the shock strut while in-service. These examples incorporate knowledge of the shock strut's stoke history in order to estimate/predict the amount of gas in solution, its percentage saturation, etc. This may permit a more refined knowledge of the true servicing state of the shock strut.
G01L 19/00 - MESURE DES FORCES, DES CONTRAINTES, DES COUPLES, DU TRAVAIL, DE LA PUISSANCE MÉCANIQUE, DU RENDEMENT MÉCANIQUE OU DE LA PRESSION DES FLUIDES - 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
G01P 7/00 - Mesure de la vitesse par intégration de l'accélération
G01P 15/00 - Mesure de l'accélération; Mesure de la décélération; Mesure des chocs, c. à d. d'une variation brusque de l'accélération
A remote towing interface is used to couple a towbar to an aircraft having a fuselage and a steerable landing gear. The remote towing interface includes a towbar coupler mounted to the aircraft and configured to releasably couple a towbar to the aircraft. The remote towing interface further includes a sensor and a controller. The sensor is configured to sense a position of the towbar relative to the aircraft when the towbar is coupled to the towbar coupler, and the controller controls the steerable landing gear according to the sensed position of the towbar relative to the aircraft.
A landing gear for a vehicle includes a strut configured for reciprocating movement between a stowed position and a deployed position. A shock absorber has a first element slidingly disposed within the strut and a second element slidingly coupled to the first element. A trailing arm is rotatably coupled to the second element. A first linkage is coupled to the first element, wherein the first linkage drives the first element between a raised position when the strut is in the stowed position and a lowered position when the strut is in the deployed position. The landing gear further includes a second linkage coupled to the trailing arm. The second linkage rotates the trailing arm between a first trailing arm position when the strut is in the stowed position and a second trailing arm position when the strut is in the deployed position.
A landing gear for a vehicle includes a strut configured for reciprocating movement between a stowed position and a deployed position. A shock absorber has a first element slidingly disposed within the strut and a second element slidingly coupled to the first element. A trailing arm is rotatably coupled to the second element. A first linkage is coupled to the first element, wherein the first linkage drives the first element between a raised position when the strut is in the stowed position and a lowered position when the strut is in the deployed position. The landing gear further includes a second linkage coupled to the trailing arm. The second linkage rotates the trailing arm between a first trailing arm position when the strut is in the stowed position and a second trailing arm position when the strut is in the deployed position.
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
A method for extending a landing gear system for a vehicle is disclosed. The landing gear system includes a first landing gear assembly and a second landing gear assembly. The method includes the steps of sensing a first load on the first landing gear assembly after the first landing gear assembly has reached a wheels-on-ground state and comparing the first load to a first target value. The method further includes the step of controlling an extension speed of the first landing gear assembly according to a difference between the first load and the first target value.
A method for extending a landing gear system for a vehicle is disclosed. The landing gear system includes a first landing gear assembly and a second landing gear assembly. The method includes the steps of sensing a first load on the first landing gear assembly after the first landing gear assembly has reached a wheels-on-ground state and comparing the first load to a first target value. The method further includes the step of controlling an extension speed of the first landing gear assembly according to a difference between the first load and the first target value.
A landing gear system includes a wheel rotatably coupled to an axle about an axis. A torque tube is rotatably mounted to the axle about the axis such that the axle extends through a central portion of the torque tube. A rotor is fixed in rotation about the axis relative to the wheel, and a stator is fixed in rotation about the axis relative to the torque tube. The landing gear assembly further includes a clutch assembly selectively reciprocal between an engaged state and a disengaged state. The stator is fixed in rotation about the axis relative to the torque tube when the clutch assembly is in an engaged state. When the clutch assembly is in a disengaged state, the stator is rotatably about the axis relative to the torque tube.
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
40.
Passive lateral stability for a maglev type vehicle
A passive lateral stability system maintains the position of a vehicle relative to a guideway. The system includes first and second guide assemblies that urge the vehicle away from first and second electrically conductive guide walls, respectively. The first guide assembly includes a wheel configured to reciprocate toward and away from the first guide wall. A biasing element bias biases the wheel toward the first guide wall. The system further includes a magnetic element associated with the wheel, wherein movement of the magnetic element relative to the first guide wall produces a magnetic force that biases the wheel away from the first guide wall. A second guide assembly is mounted to the vehicle and urges the vehicle away from the second guide wall.
A passive lateral stability system maintains the position of a vehicle relative to a guideway. The system includes first and second guide assemblies that urge the vehicle away from first and second electrically conductive guide walls, respectively. The first guide assembly includes a wheel configured to reciprocate toward and away from the first guide wall. A biasing element bias biases the wheel toward the first guide wall. The system further includes a magnetic element associated with the wheel, wherein movement of the magnetic element relative to the first guide wall produces a magnetic force that biases the wheel away from the first guide wall. A second guide assembly is mounted to the vehicle and urges the vehicle away from the second guide wall.
A landing gear system includes a wheel rotatably coupled to the axle about an axis. A motor is fixedly positioned relative to the axle with a clutch assembly operably coupled to an output shaft of the motor. The landing gear includes an actuator and a drive assembly. The actuator applies a braking force to the wheel. The drive assembly includes a pinion gear and a drive gear rotatably associated with the pinion gear. The drive gear is configured to transfer a rotational force to the wheel in order to provide autonomous taxiing capability. Both the brake assembly and the drive assembly are operably coupled to the clutch assembly so that the output shaft of the motor drives both the brake assembly and the drive assembly.
B64C 25/40 - Trains d'atterrissage caractérisés par les éléments de contact avec le sol ou une surface analogue un mouvement rotatif étant communiqué aux éléments avant l'impact
F16H 25/22 - Mécanismes à vis avec billes, rouleaux ou organes similaires entre pièces travaillant en conjugaison; Eléments essentiels pour l'utilisation de ces organes
F16D 65/18 - Mécanismes d'actionnement pour freins; Moyens pour amorcer l'opération de freinage à une position prédéterminée disposés dans, ou sur le frein adaptés pour rapprocher les organes par traction
F16D 121/24 - Type de force d'actionnement de l'actionneur Électrique ou magnétique utilisant des moteurs
A truck beam for an aircraft landing gear assembly is provided. The truck beam includes an elongate hub having first and second ends. The hub is rotatably mountable to a shock strut of the landing gear assembly. A first leg extends radially in a first direction from the first end of the hub. The first leg has an inner side facing the second end of the hub and is configured to have a first wheel rotatably mounted to the inner side about a first wheel axis. A second leg extends radially in a second direction from the second end of the hub and has an inner side facing the first end of the hub. The second leg is configured to have a second wheel rotatably mounted to the inner side of the second leg about a second wheel axis.
A disclosed method extends a support system for a maglev vehicle, the support system having at least a first landing gear assembly and a second landing gear assembly. The method includes the steps of determining a weight-on-wheels status for each of the first and the second landing gear assemblies and determining a distance from each of the first and second landing gear assemblies to a support surface. First and second extension speeds are determined for each of the first and second landing gear assemblies, respectively. The first landing gear assembly is extended at the first extension speed until the first landing gear assembly reaches a weight-on- wheels condition, and the second landing gear assembly is extended at the second extension speed until the second landing gear assembly reaches the weight-on- wheels condition.
A disclosed method extends a support system for a maglev vehicle, the support system having at least a first landing gear assembly and a second landing gear assembly. The method includes the steps of determining a weight-on-wheels status for each of the first and the second landing gear assemblies and determining a distance from each of the first and second landing gear assemblies to a support surface. First and second extension speeds are determined for each of the first and second landing gear assemblies, respectively. The first landing gear assembly is extended at the first extension speed until the first landing gear assembly reaches a weight-on-wheels condition, and the second landing gear assembly is extended at the second extension speed until the second landing gear assembly reaches the weight-on-wheels condition.
An aircraft landing gear assembly comprises a first landing gear element movably coupled relative to a second landing gear element to move between a first condition and a second condition. The aircraft landing gear assembly further comprises a fibre composite leaf spring formed from a plurality of composite layers and arranged between the first and second elements, the leaf spring being arranged to bend when the first element moves from the first condition to the second condition. The fibre composite leaf spring comprises a first region and a second region, wherein the number of composite layers in the first region is greater than the number of composite layers in the second region. The landing gear further comprises a mounting assembly arranged to engage the first region of the leaf spring to couple the leaf spring to the first landing gear element.
In some embodiments, a control unit for a vehicle is provided. The vehicle may be a maglev vehicle. The control unit is configured to autonomously control positions of landing gear on the vehicle that are extendible and retractable. In some embodiments, the control unit is configured to detect a change in a weight-on-wheels state of the vehicle, and to transition between passively controlling extension or retraction of the landing gear and actively controlling the extension distance of the landing gear in order to maintain a desired distance between the vehicle and a levitation mechanism.
In some embodiments, a control unit for a vehicle is provided. The vehicle may be a maglev vehicle. The control unit is configured to autonomously control positions of landing gear on the vehicle that are extendible and retractable. In some embodiments, the control unit is configured to detect a change in a weight-on-wheels state of the vehicle, and to transition between passively controlling extension or retraction of the landing gear and actively controlling the extension distance of the landing gear in order to maintain a desired distance between the vehicle and a levitation mechanism.
A bushing is configured for installation in the hole of a lug, which has a protrusion extending radially inward from a surface of the hole. The bushing includes a first cylindrical body that is sized to be received within the hole of the lug. A flange extends radially outward from one end of the first cylindrical body, and a first recess is formed in the first cylindrical body to a radial face. The recess is sized and configured to receive the protrusion of the lug when the bushing is installed in the hole. Engagement of the protrusion with the recess preventing movement of the bushing relative to the lug.
A taxi drive system is disclosed that provides motive force to wheels of an aircraft. The motive force is transferred by a motor powered continuous track (e.g., belt, chain, or other flexible transmission element) directly to the wheel(s) of an aircraft. The system is carried by the landing gear of the aircraft, and is placed in engagement with an aircraft wheel with sufficient force to allow for the track to drive the aircraft wheel. The taxi drive system includes a separate motor from the main aircraft engines so that the aircraft may be taxied while the main engines are shutdown or at idle.
B64C 25/40 - Trains d'atterrissage caractérisés par les éléments de contact avec le sol ou une surface analogue un mouvement rotatif étant communiqué aux éléments avant l'impact
51.
CLUTCH ASSEMBLY FOR AUTONOMOUS TAXIING OF AIRCRAFT
A landing gear system includes an axle having an internal cavity and a wheel rotatably coupled to the axle. A drive shaft is mounted within the cavity to be rotatable about an axis. The landing gear system further includes a rod slidably mounted within the drive shaft and a clutch. The clutch has a first portion that is coupled to the rod and rotates with the drive shaft. A second portion of the clutch is fixedly coupled to the wheel. The rod selectively reciprocates along the axis between a first position and a second position to engage and disengage the clutch.
B64C 25/36 - Aménagements ou adaptations des roues, des pneumatiques ou des essieux
F16D 11/14 - Embrayages dans lesquels les organes ont des parties qui se pénètrent mutuellement avec des organes d'embrayage mobiles selon l'axe uniquement
A thermal actuator includes a piston slidingly within a cylinder. The piston cooperates with the cylinder to define a cavity. The piston also includes a rod extending away from the cavity. A magnetic field generator selectively imparts an alternating magnetic field to the cylinder, and inductively heats a heating element mounted within the cavity. The cavity also includes a volume of a phase-change material, which is melted by the heating element. The melting phase-change material expands to drive the rod from a retracted position to an extended position.
F03G 7/06 - Mécanismes produisant une puissance mécanique, non prévus ailleurs ou utilisant une source d'énergie non prévue ailleurs utilisant la dilatation ou la contraction des corps produites par le chauffage, le refroidissement, l'humidification, le séchage ou par des phénomènes similaires
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
F03G 7/04 - Mécanismes produisant une puissance mécanique, non prévus ailleurs ou utilisant une source d'énergie non prévue ailleurs utilisant les différences de pression ou les différences thermiques existant dans la nature
53.
Wheeled vehicle station docking using a kneeling landing gear system
A method is disclosed for docking and undocking a hyperloop vehicle in a station. The method includes the step of extending a support system to a first position, wherein the support system engages a surface to support the hyperloop vehicle at a first elevation. The method further includes the steps of moving the hyperloop vehicle to a predetermined docking position and engaging a coupler to fixedly position the hyperloop vehicle relative to a docking platform.
A bushing is configured for installation in the hole of a lug, which has a protrusion extending radially inward from a surface of the hole. The bushing includes a first cylindrical body that is sized to be received within the hole of the lug. A flange extends radially outward from one end of the first cylindrical body, and a first recess is formed in the first cylindrical body to a radial face. The recess is sized and configured to receive the protrusion of the lug when the bushing is installed in the hole. Engagement of the protrusion with the recess preventing movement of the bushing relative to the lug.
A method is disclosed for docking and undocking a hyperloop vehicle in a station. The method includes the step of extending a support system to a first position, wherein the support system engages a surface to support the hyperloop vehicle at a fist elevation. The method further includes the steps of moving the hyperloop vehicle to a predetermined docking position and engaging a coupler to fixedly position the hyperloop vehicle relative to a docking platform.
A landing gear system includes an axle having an internal cavity and a wheel rotatably coupled to the axle. A drive shaft is mounted within the cavity to be rotatable about an axis. The landing gear system further includes a rod slidably mounted within the drive shaft and a clutch. The clutch has a first portion that is coupled to the rod and rotates with the drive shaft. A second portion of the clutch is fixedly coupled to the wheel. The rod selectively reciprocates along the axis between a first position and a second position to engage and disengage the clutch.
B64C 25/40 - Trains d'atterrissage caractérisés par les éléments de contact avec le sol ou une surface analogue un mouvement rotatif étant communiqué aux éléments avant l'impact
Shield assemblies for an aircraft landing gear include an aerodynamic shield, a first support bracket assembly, and a second support bracket assembly. The first support bracket assembly is configured to couple with a structural member of the aircraft landing gear, to support a first end of the aerodynamic shield, and to have a first position that is fixed relative to the structural member in an x-direction, a y-direction, and a z-direction. The first support bracket assembly has a first clamp that is configured to fix the first support bracket assembly relative to the structural member in the x-direction. The second support bracket assembly is configured to support a second end of the aerodynamic shield and to have a second position that is fixed relative to the structural member in the y-direction and the z-direction.
Shield assemblies for an aircraft landing gear include an aerodynamic shield, a first support bracket assembly, and a second support bracket assembly. The first support bracket assembly is configured to couple with a structural member of the aircraft landing gear, to support a first end of the aerodynamic shield, and to have a first position that is fixed relative to the structural member in an x-direction, a y-direction, and a z-direction. The first support bracket assembly has a first clamp that is configured to fix the first support bracket assembly relative to the structural member in the x-direction. The second support bracket assembly is configured to support a second end of the aerodynamic shield and to have a second position that is fixed relative to the structural member in the y-direction and the z-direction.
A shock strut is provided that includes a first energy absorption stage or load limiter and a second energy absorption stage or load limiter. The second energy absorption stage or load limiter includes one or more disc springs (205). The shock strut can be employed on both fixed and retractable landing gear alike, while providing design adjustability for obtaining load-deflection curves that accommodate a range of descent or impact velocities.
F16F 9/58 - Butées pour limiter la course, p.ex. disposées sur la tige de piston à l'extérieur du cylindre
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 9/49 - Tampons arrêtoirs limitant le passage du fluide, p.ex. tampons hydrauliques
An aircraft landing gear includes a shock strut with a rod slidably received within a cylinder. A beam is rotatably mounted to the rod, and wheels are mounted to the beam. The landing gear further includes a link assembly with an upper link and a lower link. The upper link has a first end rotatably connected to the cylinder, and the lower link has a first end rotatably connected to the beam. The second ends of the upper and lower links are rotatably coupled to each other by a limiter joint. The limiter joint includes a first stop associated with the upper link and a second stop associated with the lower link. The stops are configured such that the first stop engages the second stop to limit rotation of the upper link relative to the lower link.
An aircraft landing gear includes a shock strut with a rod slidably received within a cylinder. A beam is rotatably mounted to the rod, and wheels are mounted to the beam. The landing gear further includes a link assembly with an upper link and a lower link. The upper link has a first end rotatably connected to the cylinder, and the lower link has a first end rotatably connected to the beam. The second ends of the upper and lower links are rotatably coupled to each other by a limiter joint. The limiter joint includes a first stop associated the upper link and a second stop associated with the lower link. The stops are configured such that the first stop engages the second stop to limit rotation of the upper link relative to the lower link.
A structural component, or parts thereof, for a machine system or vehicle, such as an aircraft, is provided. In some examples, the structural component includes at least one embedded passageway or line. In other examples, the passageway or line is formed integrally on the exterior surface of the structural component. In some of these examples, the structural component can benefit from additive manufacturing techniques or methodologies.
F16C 7/00 - Bielles ou organes de liaisons similaires pivotant aux deux extrémités; Structure des pieds de bielles
F16L 3/26 - Supports pour tuyaux, pour câbles ou pour conduits de protection, p.ex. potences, pattes de fixation, attaches, brides, colliers spécialement adaptés pour le support des tuyaux sur toute leur longueur, p.ex. chenal ou conduite de tuyaux
F16S 3/00 - Eléments allongés, p.ex. éléments profilés; Leurs assemblages; Armatures ou grilles
63.
Slow response solenoid hydraulic valve, and associated systems and methods
Hydraulic valves for dampening pressure spikes and associated methods are disclosed herein. In one embodiment, a hydraulic valve for dampening pressure spikes includes: a spool configured to move axially inside the hydraulic valve; and a sleeve configured to at least partially house the spool. A location of the spool with respect to the sleeve may determine a flow of a working fluid through the hydraulic valve. A viscous damper is at least partially housed inside an opening in the spool, and a viscous friction between the viscous damper and the opening in the spool slows a motion of the spool.
F16K 11/07 - 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 tiroirs à éléments de fermeture glissant linéairement à glissières cylindriques
F15B 13/04 - Dispositifs de distribution ou d'alimentation du fluide caractérisés par leur adaptation à la commande de servomoteurs pour utilisation avec un servomoteur unique
B60T 8/36 - Dispositions pour adapter la force de freinage sur la roue aux conditions propres au véhicule ou à l'état du sol, p.ex. par limitation ou variation de la force de freinage selon une condition de vitesse, p.ex. accélération ou décélération comportant un régulateur de pression fluidique répondant à une condition de vitesse comportant un clapet-pilote sensible à une force électromagnétique
B60T 8/50 - Dispositions pour adapter la force de freinage sur la roue aux conditions propres au véhicule ou à l'état du sol, p.ex. par limitation ou variation de la force de freinage selon une condition de vitesse, p.ex. accélération ou décélération comportant un régulateur de pression fluidique répondant à une condition de vitesse comportant des moyens pour commander la valeur à laquelle la pression est de nouveau appliquée au frein
B60T 11/34 - Valves réduisant ou limitant la pression
F16K 47/00 - Moyens incorporés aux soupapes pour absorber l'énergie d'un fluide
64.
SLOW RESPONSE SOLENOID HYDRAULIC VALVE, AND ASSOCIATED SYSTEMS AND METHODS
Hydraulic valves for dampening pressure spikes and associated methods are disclosed herein. In one embodiment, a hydraulic valve for dampening pressure spikes includes: a spool configured to move axially inside the hydraulic valve; and a sleeve configured to at least partially house the spool. A location of the spool with respect to the sleeve may determine a flow of a working fluid through the hydraulic valve. A viscous damper is at least partially housed inside an opening in the spool, and a viscous friction between the viscous damper and the opening in the spool slows a motion of the spool.
F16K 47/02 - Moyens incorporés aux soupapes pour absorber l'énergie d'un fluide pour empêcher les coups de bélier ou le bruit
F15C 3/02 - Eléments de circuits ayant des parties en mouvement utilisant des clapets à bobines
F16K 3/24 - Robinets-vannes ou tiroirs, c. à d. dispositifs obturateurs dont l'élément de fermeture glisse le long d'un siège pour l'ouverture ou la fermeture à faces d'obturation en forme de surfaces de solides de révolution avec corps de tiroir cylindrique
F16K 3/30 - Robinets-vannes ou tiroirs, c. à d. dispositifs obturateurs dont l'élément de fermeture glisse le long d'un siège pour l'ouverture ou la fermeture - Détails
F16K 11/07 - 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 tiroirs à éléments de fermeture glissant linéairement à glissières cylindriques
F16K 31/124 - Moyens de fonctionnement; Dispositifs de retour à la position de repos actionnés par un fluide le fluide agissant sur un piston servo-commandé
A torque link assembly for a landing gear includes a lower torque link and an upper torque link that releasably engage first and second quick release pin assemblies. The pin assemblies each include a housing attached to one of the torque links, and a locking pin member extending through the housing. The locking pin member includes a rod portion and a pin portion, and is slidable between an engaged position and a disengaged position for hingedly connecting/disconnecting the torque links. One of the housing and the locking pin member includes a channel having a longitudinal portion and a circumferential portion, and the other has a guide pin that engages the channel. The guide pin is in the longitudinal portion of the channel when moving between the engaged and disengaged positions, and is retained in the disengaged position when the guide pin is in the circumferential portion of the channel.
F16B 21/00 - 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'entoure; Fixations à ergots et douilles largables sans filetage
A torque link assembly for a landing gear includes a lower torque link and an upper torque link that releasably engage first and second quick release pin assemblies. The pin assemblies each include a housing attached to one of the torque links, and a locking pin member extending through the housing. The locking pin member includes a rod portion and a pin portion, and is slidable between an engaged position and a disengaged position for hingedly connecting/disconnecting the torque links. One of the housing and the locking pin member includes a channel having a longitudinal portion and a circumferential portion, and the other has a guide pin that engages the channel. The guide pin is in the longitudinal portion of the channel when moving between the engaged and disengaged positions, and is retained in the disengaged position when the guide pin is in the circumferential portion of the channel.
A fitting assembly includes a fitting with at least one a pocket. The pocket includes a web extending inward from a perimeter of the pocket, and the web has cutout that defines an inner edge. A stiffener is mounted within the pocket. The stiffener includes a lattice and a coupler that is configured to engage at least a portion of the web to mount the lattice to the fitting.
E04C 3/08 - Poutrelles; Solives, fermes ou structures analogues à des fermes, p.ex. préfabriquées; Linteaux; Traverses métalliques à âme découpée, p.ex. à âme formée d'éléments analogues à des barreaux; Fermes métalliques en treillage
B64C 25/32 - Trains d'atterrissage caractérisés par les éléments de contact avec le sol ou une surface analogue
B64C 25/14 - Atterrisseurs non fixes, p.ex. largables escamotables, repliables ou ayant un mouvement apparenté d'avant en arrière
E04C 3/02 - Poutrelles; Solives, fermes ou structures analogues à des fermes, p.ex. préfabriquées; Linteaux; Traverses
A fitting assembly includes a fitting with at least one a pocket. The pocket includes a web extending inward from a perimeter of the pocket, and the web has cutout that defines an inner edge. A stiffener is mounted within the pocket. The stiffener includes a lattice and a coupler that is configured to engage at least a portion of the web to mount the lattice to the fitting.
A torque link assembly for a shock strut includes an upper torque link that is selectively retained in a stowed position when uncoupled from a lower torque link. The upper torque link includes first and second coaxial lugs that rotatably couple the upper torque link to an alignment feature. A latch mechanism includes a latch fitting rotatably coupled to either the upper torque link or the alignment feature. The latch mechanism further includes a stop fitting fixedly coupled to the other of the upper torque link and the alignment feature. The latch fitting engages the stop fitting to maintain the upper torque link in the stowed position. At least one of the latch fitting and stop fitting is positioned between the first and second lugs of the upper torque link.
F16F 9/18 - Dispositifs à un ou plusieurs organes, p.ex. des pistons, des aubes, se déplaçant en va-et-vient dans des chambres et utilisant un effet d'étranglement comportant uniquement un déplacement rectiligne des parties travaillant avec un cylindre fermé et un piston déterminant, à l’intérieur de ce cylindre, plusieurs espaces de travail
B64C 25/10 - Atterrisseurs non fixes, p.ex. largables escamotables, repliables ou ayant un mouvement apparenté
B64C 25/58 - Aménagements ou adaptations des amortisseurs ou des ressorts
F16B 2/20 - Clips, c. à d. dispositifs de fixation à serrage effectué uniquement par la résistance à la déformation inhérente au matériau dont est fait le dispositif
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
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
A torque link assembly for a shock strut includes an upper torque link that is selectively retained in a stowed position when uncoupled from a lower torque link. The upper torque link includes first and second coaxial lugs that rotatably couple the upper torque link to an alignment feature. A latch mechanism includes a latch fitting rotatably coupled to either the upper torque link or the alignment feature. The latch mechanism further includes a stop fitting fixedly coupled to the other of the upper torque link and the alignment feature. The latch fitting engages the stop fitting to maintain the upper torque link in the stowed position. At least one of the latch fitting and stop fitting is positioned between the first and second lugs of the upper torque link.
A shock absorber with lubricated bearings for an aircraft landing gear includes a piston that is received in a cylinder, and an upper bearing fixed to the piston that slidably engages an inner surface of the cylinder. A lower bearing extends inwardly from a lower portion of the cylinder and engages an outer surface of the piston. The lower bearing has a center axis and defines an annular bearing surface configured to slidably engage the piston outer surface. The annular bearing surface has a first portion that extends circumferentially more than one hundred eighty degrees about the center axis at a constant radius, defining a circular annular segment. A second portion closes the circular annular segment and defines a shallow channel or pocket in the annular bearing surface. In some embodiments the lower bearing further comprises oppositely disposed frustoconical thrust portions.
F16F 7/09 - Amortisseurs de vibrations; Amortisseurs de chocs avec surfaces de friction à déplacement rectiligne l'une le long de l'autre dans des amortisseurs du type cylindre-piston
F16C 33/10 - Structures relatives à la lubrification
F16F 7/112 - Amortisseurs de vibrations; Amortisseurs de chocs utilisant un effet d'inertie l'élément d'inertie étant monté de manière élastique sur des ressorts à fluide
72.
LUBRICATION MECHANISM DESIGN FOR AIRCRAFT LANDING GEAR BEARINGS
A shock absorber with lubricated bearings for an aircraft landing gear includes a piston that is received in a cylinder, and an upper bearing fixed to the piston that slidably engages an inner surface of the cylinder. A lower bearing extends inwardly from a lower portion of the cylinder and engages an outer surface of the piston. The lower bearing has a center axis and defines an annular bearing surface configured to slidably engage the piston outer surface. The annular bearing surface has a first portion that extends circumferentially more than one hundred eighty degrees about the center axis at a constant radius, defining a circular annular segment. A second portion closes the circular annular segment and defines a shallow channel or pocket in the annular bearing surface. In some embodiments the lower bearing further comprises oppositely disposed frustoconical thrust portions.
A shock strut for a vehicle includes a housing with a through channel and a motor mount, and a motor fixed to the housing. The cylinder of a shock strut is configured to define a lead screw on its outer surface. The cylinder extends through the housing. The piston of the shock strut is attached to a ground engaging assembly. A gear nut rotatably mounted in the housing threadably engages the threaded cylinder, and is configured to be driven by the motor. The housing is attached to the vehicle, and the gear nut is controllably rotated to extend and retract the shock strut. A sensor provided on the assembly monitors the position of the shock strut. A torsion link assembly reacts rotational forces on the cylinder.
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 9/56 - Moyens pour régler la longueur du ressort ou de l'amortisseur, ou pour les bloquer, p.ex. en fin de course
A shock strut for a vehicle includes a housing with a through channel and a motor mount, and a motor fixed to the housing. The cylinder of a shock strut is configured to define a lead screw on its outer surface. The cylinder extends through the housing. The piston of the shock strut is attached to a ground engaging assembly. A gear nut rotatably mounted in the housing threadably engages the threaded cylinder, and is configured to be driven by the motor. The housing is attached to the vehicle, and the gear nut is controllably rotated to extend and retract the shock strut. A sensor provided on the assembly monitors the position of the shock strut. A torsion link assembly reacts rotational forces on the cylinder.
B60G 17/00 - Suspensions élastiques permettant d'ajuster les caractéristiques des ressorts ou des amortisseurs de vibrations, de réguler la distance entre la surface porteuse et la partie suspendue du véhicule ou de bloquer la suspension pendant l'utilisation pou
Hydraulic valves for dampening pressure spikes and associated methods are disclosed herein. In one embodiment, a hydraulic valve for dampening pressure spikes includes a valve body, a poppet at least partially inside the valve body, and a pilot piston at least partially inside the valve body and away from the poppet. The pilot piston contacts the poppet in response to a pressure spike.
F16K 17/04 - Soupapes ou clapets de sûreté; Soupapes ou clapets d'équilibrage fermant sur insuffisance de pression d'un côté actionnés par ressort
F16F 9/512 - Moyens réagissant à l'action de la charge sur l'amortisseur ou à la pression de fluide dans l'amortisseur
F16F 9/46 - 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 permettant la commande à distance
F16K 17/08 - Soupapes ou clapets de sûreté; Soupapes ou clapets d'équilibrage fermant sur insuffisance de pression d'un côté actionnés par ressort avec dispositions particulières pour réaliser une large ouverture d'évacuation
F16K 17/26 - Soupapes ou clapets limiteurs de débit fonctionnant par différence de pression entre deux points de l'écoulement et agissant directement sur l'élément d'obturation dans les deux sens
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
F16K 17/10 - Soupapes ou clapets de sûreté; Soupapes ou clapets d'équilibrage fermant sur insuffisance de pression d'un côté actionnés par ressort avec soupape auxiliaire agissant par un fluide sur la soupape principale
F16L 55/045 - Dispositifs amortisseurs de vibrations ou de pulsations dans les fluides spécialement conçus pour prévenir ou atténuer les effets des coups de bélier
A retractable landing gear includes a main strut having an upper end that is configured to connect to aircraft primary structure and a lower end configured to connect to an axle or bogie truck. An articulated stay has a distal end configured to connect to the aircraft structure and a proximal end pivotally connected to a cardan pin member. The cardan pin member has a cylindrical portion with a first recessed annular channel. The cardan pin member is retained in the socket by a ring assembly formed by two semi-annular ring members that slidably engages the first recessed channel. The ring assembly defines a second recessed annular channel. A collar is configured to be positioned over the second recessed channel, and to contract upon a change in temperature to lockingly engage the second recessed channel, to secure the split ring assembly in the first recessed channel.
B64C 25/26 - Systèmes de commande ou de verrouillage à cet effet
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
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
B64C 25/12 - Atterrisseurs non fixes, p.ex. largables escamotables, repliables ou ayant un mouvement apparenté latéralement
A retractable landing gear includes a main strut having an upper end that is configured to connect to aircraft primary structure and a lower end configured to connect to an axle or bogie truck. An articulated stay has a distal end configured to connect to the aircraft structure and a proximal end pivotally connected to a cardan pin member. The cardan pin member has a cylindrical portion with a first recessed annular channel. The cardan pin member is retained in the socket by a ring assembly formed by two semi- annular ring members that slidably engages the first recessed channel. The ring assembly defines a second recessed annular channel. A collar is configured to be positioned over the second recessed channel, and to contract upon a change in temperature to lockingly engage the second recessed channel, to secure the split ring assembly in the first recessed channel.
F16B 21/18 - 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'entoure; Fixations à ergots et douilles largables sans filetage à parties séparées par gorges ou encoches pratiquées dans l'axe ou l'arbre - Détails
78.
HYDRAULIC VALVE FOR DAMPENING PRESSURE SPIKES, AND ASSOCIATED SYSTEMS AND METHODS
Hydraulic valves for dampening pressure spikes and associated methods are disclosed herein. In one embodiment, a hydraulic valve for dampening pressure spikes includes a valve body, a poppet at least partially inside the valve body, and a pilot piston at least partially inside the valve body and away from the poppet. The pilot piston contacts the poppet in response to a pressure spike.
F16K 17/36 - Soupapes ou clapets de sûreté; Soupapes ou clapets d'équilibrage fonctionnant sous l'action de circonstances extérieures, p.ex. un choc, un changement de position
F16K 17/04 - Soupapes ou clapets de sûreté; Soupapes ou clapets d'équilibrage fermant sur insuffisance de pression d'un côté actionnés par ressort
A linear telescopic actuator (1) that comprises a cylinder (2), a sliding part (3), a spring seat (4) and a first compression spring (5) capable of resiliently opposing the sliding part (3) approaching the spring seat (4). The spring seat (4) presents an outer annular groove (6) and the cylinder (2) includes an inner annular groove (7). The actuator (1) also presents a blocking part (8), the actuator (1) being adapted to adopt selectively an assembled configuration and a disassembled configuration. The blocking part (8) in the assembled configuration is engaged inside the inner and outer annular grooves (6, 7). The blocking part (8) in the disassembled configuration being disengaged from one of the grooves so as to allow spring seat (4) to slide in the cylinder (2).
F03G 1/10 - Autres parties constitutives ou détails pour la production d'un mouvement de sortie autre que rotatif, p.ex. vibratoire
F15B 15/14 - Dispositifs actionnés par fluides pour déplacer un organe d'une position à une autre; Transmission associée à ces dispositifs caractérisés par la structure de l'ensemble moteur le moteur étant du type à cylindre droit
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 quenching agent delivery apparatus is provided for delivering a quenching agent to a component to be quenched. The delivery apparatus comprises an inlet through which the quenching agent is configured to be delivered into the apparatus, a first outlet configured to deliver quenching agent in a first direction to an inner surface of the component, and a second outlet configured to deliver quenching agent in a second direction to an inner surface of the component.
C21D 1/667 - Dispositifs pour trempe pour la trempe par pulvérisation
C21D 1/63 - Dispositifs pour trempe pour bains de trempe
C21D 1/56 - Procédés ou dispositifs généraux pour le traitement thermique, p.ex. recuit, durcissement, trempe ou revenu caractérisés par les agents de trempe
Safran Landing Systems Canada Inc./ Safran Systèmes d'Atterrissage Canada Inc. (Canada)
Inventeur(s)
Besliu, Marin
Bryant, Chris
Smith, Howard
Abrégé
Described is a modular linear actuator for use in an aerospace application, comprising: a piston housing having a closed end and an open end; a piston rod slideable within an interior of the piston housing between an extended position and a compressed position, the piston rod having a first end proximal to the closed end of the piston housing and a second end distal to the closed end of the piston housing; an attachment mechanism for removably attaching a lug end to the closed end of the piston housing, the lug end for attaching the actuator to a first component; an attachment mechanism for removably attaching a rod end to the second end of the piston rod, the rod end for attaching the piston rod to a second component; and, a piston head removably attached to the first end of the piston rod, the piston head for providing a snubbing engagement with the closed end of the piston housing.
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
F15B 15/14 - Dispositifs actionnés par fluides pour déplacer un organe d'une position à une autre; Transmission associée à ces dispositifs caractérisés par la structure de l'ensemble moteur le moteur étant du type à cylindre droit
F15B 15/22 - Autres parties constitutives pour accélérer ou ralentir le mouvement
F16B 3/04 - Assemblages du type par clavette; Clavettes utilisant des clavettes, en fil métallique ou autre matériau flexible, introduites par une ouverture donnant accès aux rainures pratiquées dans les surfaces adjacentes des parties à assembler
F16J 1/12 - Liaison avec les organes d'entraînement avec les tiges de piston, c. à d. liaisons rigides
A quenching agent delivery apparatus is provided for delivering a quenching agent to a component to be quenched. The delivery apparatus comprises an inlet through which the quenching agent is configured to be delivered into the apparatus, a first outlet configured to deliver quenching agent in a first direction to an inner surface of the component, and a second outlet configured to deliver quenching agent in a second direction to an inner surface of the component.
SAFRAN LANDING SYSTEMS CANADA INC. / SAFRAN SYSTEMES D'ATTERRISSAGE CANADA INC. (Canada)
Inventeur(s)
Schmidt, Kyle
Abrégé
A proximity sensor for detecting non-contact detection of a target using a fibre optic strain sensor and a system for operating multiple such proximity sensors is disclosed. The proximity sensor includes an optic fibre that has an optic fibre strain sensor that is coupled to a mass that moves in response to the target. The mass can be a magnet that moves when a ferrous target is within the magnetic field of the magnet causing the magnet to move and apply strain to the optic fibre strain sensor. The optic strain sensor can include periodic variation in the refractive index of the optic fibre, such as a fibre Bragg grating. The proximity sensor can include a second fibre optic sensor that is sensitive to temperature or a second fibre optic strain sensor coupled to a second magnet that operates in opposition to the first magnet. A system coupling multiple proximity sensors can include an interrogator that has an optical power source and a detector, each coupled to a processor. The processor compares frequency information from the proximity sensor to a threshold to determine whether a target is in proximity to its corresponding proximity sensor.
G01V 3/08 - Prospection ou détection électrique ou magnétique; Mesure des caractéristiques du champ magnétique de la terre, p.ex. de la déclinaison ou de la déviation fonctionnant au moyen de champs magnétiques ou électriques produits ou modifiés par les objets ou les structures géologiques, ou par les dispositifs de détection
B64C 25/28 - Systèmes de commande ou de verrouillage à cet effet avec dispositifs indicateurs ou avertisseurs
Safran Landing Systems Canada Inc./Safran Systemes D'Atterrissage Canada Inc. (Canada)
Inventeur(s)
Schmidt, Robert Kyle
Abrégé
A proximity sensor for detecting non-contact detection of a target using a fiber optic strain sensor and a system for operating multiple such proximity sensors is disclosed. The proximity sensor includes an optic fiber that has an optic fiber strain sensor that is coupled to a mass that moves in response to the target. The mass can be a magnet that moves when a ferrous target is within the magnetic field of the magnet causing the magnet to move and apply strain to the optic fiber strain sensor. The optic strain sensor can include periodic variation in the refractive index of the optic fiber, such as a fiber Bragg grating. The proximity sensor can include a second fiber optic sensor that is sensitive to temperature or a second fiber optic strain sensor coupled to a second magnet that operates in opposition to the first magnet. A system coupling multiple proximity sensors can include an interrogator that has an optical power source and a detector, each coupled to a processor. The processor compares frequency information from the proximity sensor to a threshold to determine whether a target is in proximity to its corresponding proximity sensor.
G01B 11/16 - Dispositions pour la mesure caractérisées par l'utilisation de techniques optiques pour mesurer la déformation dans un solide, p.ex. indicateur optique de déformation
G01V 3/08 - Prospection ou détection électrique ou magnétique; Mesure des caractéristiques du champ magnétique de la terre, p.ex. de la déclinaison ou de la déviation fonctionnant au moyen de champs magnétiques ou électriques produits ou modifiés par les objets ou les structures géologiques, ou par les dispositifs de détection
G01K 11/32 - Mesure de la température basée sur les variations physiques ou chimiques, n'entrant pas dans les groupes , , ou utilisant des changements dans la transmittance, la diffusion ou la luminescence dans les fibres optiques
SAFRAN LANDING SYSTEMS CANADA INC. / SAFRAN SYSTEMES D'ATTERRISSAGE CANADA INC. (Canada)
Inventeur(s)
Beslu, Marin
Bryant, Chris
Smith, Howard
Abrégé
Described is a modular linear actuator for use in an aerospace application, comprising: a piston housing having a closed end and an open end; a piston rod slideable within an interior of the piston housing between an extended position and a compressed position, the piston rod having a first end proximal to the closed end of the piston housing and a second end distal to the closed end of the piston housing; an attachment mechanism for removably attaching a lug end to the closed end of the piston housing, the lug end for attaching the actuator to a first component; an attachment mechanism for removably attaching a rod end to the second end of the piston rod, the rod end for attaching the piston rod to a second component; and, a piston head removably attached to the first end of the piston rod, the piston head for providing a snubbing engagement with the closed end of the piston housing.
F15B 15/14 - Dispositifs actionnés par fluides pour déplacer un organe d'une position à une autre; Transmission associée à ces dispositifs caractérisés par la structure de l'ensemble moteur le moteur étant du type à cylindre droit
F15B 15/22 - Autres parties constitutives pour accélérer ou ralentir le mouvement
F16J 1/00 - Pistons; Pistons à fourreau; Plongeurs
F16J 1/09 - Pistons; Pistons à fourreau; Plongeurs comprenant des moyens de guidage des fluides
SAFRAN LANDING SYSTEMS CANADA INC. / SAFRAN SYSTEMES D'ATTERRISSAGE CANADA INC. (Canada)
Inventeur(s)
Voiculescu, Dan Amariei
Leung, Ernest
Abrégé
locking mechanism for locking an actuator piston within an actuator cylinder housing is disclosed. The locking mechanism comprises a locking pin that is moveable between extended and retracted positions. The locking pin can be moved using a controller, such as a hydraulic controller, for example. In the extended position the locking pin engages the actuator piston thereby locking the actuator piston in a specific position. The locking mechanism includes a mechanical bias (such as a spring or other mechanical system) that biases the locking pin towards an extended position to lock the actuator piston when counter-pressure on the locking pin is lower than the pressure provided by the mechanical bias. The locking pin can be hydraulically operated so that hydraulic pressure that forces the actuator piston to retract also exerts force on the locking pin to move it from a locked position to an unlocked position.
SAFRAN LANDING SYSTEMS CANADA INC./SAFRAN SYSTEMES D'ATTERRISSAGE CANADA INC. (Canada)
Inventeur(s)
Voiculescu, Dan Amariei
Leung, Ernest
Abrégé
A locking mechanism for locking an actuator piston within an actuator cylinder housing is disclosed. The locking mechanism comprises a locking pin that is moveable between extended and retracted positions. The locking pin can be moved using a controller, such as a hydraulic controller, for example. In the extended position the locking pin engages the actuator piston thereby locking the actuator piston in a specific position. The locking mechanism includes a mechanical bias (such as a spring or other mechanical system) that biases the locking pin towards an extended position to lock the actuator piston when counter-pressure on the locking pin is lower than the pressure provided by the mechanical bias. The locking pin can be hydraulically operated so that hydraulic pressure that forces the actuator piston to retract also exerts force on the locking pin to move it from a locked position to an unlocked position.
SAFRAN LANDING SYSTEMS CANADA INC./SAFRAN SYSTEMES D'ATTERRISSAGE CANADA INC. (Canada)
Inventeur(s)
Ataman, Gary
Abrégé
A switch assembly is disclosed having a switch with an actuator moveable from an armed position to a disarmed position. A housing is attached to the switch and contains a cam that holds the switch actuator in the armed position. A trigger makes contact with the cam causing it to rotate within the housing and allowing the actuator to extend to move to a disarmed position. In some variants the cam can be shaped to prevent manual rotation against the bias force of the actuator in the disarmed position. The switch assembly can be positioned on an aircraft landing gear to detect an over-steer occurrence where the landing gear may become damaged. The state of the switch can be visibly or audibly indicated by an indicator in the aircraft cockpit or other location visible/audible to the ground operators.
H01H 3/16 - Organes moteurs, c. à d. pour actionner le mécanisme d'entraînement par une force mécanique extérieure à l'interrupteur adaptés pour être actionnés dans une position limite ou autre position prédéterminée dans le trajet d'un corps, le mouvement relatif de l'interrupteur et du corps ayant principalement un autre but que d'actionner l'interrupteur, p.ex. un interrupteur
A hydraulic shimmy damper that resolves drawbacks in several known shimmy dampers, such as damping characteristics that are dependent on oil temperature variations. The disclosed shimmy damper includes a hydraulic compensator (40) having an internal fluid volume that is significantly more important than a fluid volume expelled from the body of the shimmy damper when its piston moves fore and aft. The shimmy damper also includes a hydraulic manifold (30) arranged between the body and the hydraulic compensator and defining a transfer channel between chambers in the piston that is connected to the hydraulic compensator. The manifold receives interchangeable hydraulic cartridge-type valves (CV1,RV1; CV2,RV2) for metering the fluid flowing from the chambers to the transfer channel, and allows the fluid to freely enter the chambers from the transfer channel. The present shimmy damper is therefore much less sensitive to oil temperature variation under intense shimmy.
B64C 25/50 - Atterrisseurs orientables; Amortissement du shimmy
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
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 13/00 - Ensembles comportant des ressorts du type non à fluide ainsi que des amortisseurs de vibrations, des amortisseurs de chocs ou des ressorts à fluide
Disclosed is an electric accumulator for selectively operating at least one aircraft device. The electric accumulator includes an ultra-capacitor array for storing electrical energy, which can later be used to power an aircraft device. The stored electrical energy can also be used as a source of emergency backup power. The distribution of the electrical energy is controlled by a power distribution controller. The electric accumulator may be charged by a power source on an aircraft, or it may be pre-charged by an external power source.
B60L 1/00 - Fourniture de l'énergie électrique à l'équipement auxiliaire des véhicules à traction électrique
H02J 7/00 - Circuits pour la charge ou la dépolarisation des batteries ou pour alimenter des charges par des batteries
H02J 9/00 - Circuits pour alimentation de puissance de secours ou de réserve, p.ex. pour éclairage de secours
H02J 9/06 - Circuits pour alimentation de puissance de secours ou de réserve, p.ex. pour éclairage de secours dans lesquels le système de distribution est déconnecté de la source normale et connecté à une source de réserve avec commutation automatique
H02J 7/34 - Fonctionnement en parallèle, dans des réseaux, de batteries avec d'autres sources à courant continu, p.ex. batterie tampon
92.
Method and system for health monitoring of aircraft landing gear
SAFRAN LANDING SYSTEMS CANADA INC./SAFRAN SYSTEMES D'ATTERRISSAGE CANADA INC. (Canada)
Inventeur(s)
Schmidt, R. Kyle
Gedeon, Steven A.
Abrégé
The invention relates to a new method and system for health monitoring of aircraft landing gear. The system includes sensors that are attached to the landing gear structure and equipment (e.g., one or more of brakes, tires, hydraulics, electrical systems and switches) and analyzed to report and alert personnel such as pilots, maintenance personnel, airline operators, ground crew and regulatory authorities of the health of the landing gear and the potential need for service, maintenance or replacement. The system monitors and reports critical health issues as real-time information which can be analyzed in conjunction with an extensive database of information and used to alert pilots or other relevant personnel to the condition of the landing gear and actions that may be required as a result.
SAFRAN LANDING SYSTEMS CANADA INC./SAFRAN SYSTEMES D'ATTERRISSAGE CANADA INC. (Canada)
Inventeur(s)
Schmidt, Robert Kyle
El-Samid, Nader Abu
Abrégé
The present invention provides a structural deflection and load measuring device for mounting on an axle. The device includes at least one light beam emitting device connected to the axle and able to emit at least one light beam and at least one light position sensing device connected to the axle. The sensing device is located relative to the light beam emitting device for receiving at least one light beam from the light beam emitting device thereon and is operable to calculate the position of the light beam received on its surface.
G01L 1/24 - Mesure des forces ou des contraintes, en général en mesurant les variations des propriétés optiques du matériau quand il est soumis à une contrainte, p.ex. par l'analyse des contraintes par photo-élasticité
94.
Electric accumulator utilizing an ultra-capacitor array
SAFRAN LANDING SYSTEMS CANADA INC./SAFRAN SYSTEMES D'ATTERRISSAGE CANADA INC. (Canada)
Inventeur(s)
Brookfield, Chris
Abrégé
Disclosed is an electric accumulator for selectively operating at least one aircraft device. The electric accumulator includes an ultra-capacitor array for storing electrical energy, which can later be used to power an aircraft device. The stored electrical energy can also be used as a source of emergency backup power. The distribution of the electrical energy is controlled by a power distribution controller. The electric accumulator may be charged by a power source on an aircraft, or it may be pre-charged by an external power source.
SAFRAN LANDING SYSTEMS CANADA INC. / SAFRAN SYSTEMES D'ATTERRISSAGE CANADA INC. (Canada)
Inventeur(s)
Brookfield, Chris
Abrégé
Disclosed is an electric accumulator for selectively operating at least one aircraft device. The electric accumulator includes an ultra-capacitor array for storing electrical energy, which can later be used to power an aircraft device. The stored electrical energy can also be used as a source of emergency backup power. The distribution of the electrical energy is controlled by a power distribution controller. The electric accumulator may be charged by a power source on an aircraft, or it may be pre-charged by an external power source.
SAFRAN LANDING SYSTEMS CANADA INC./SAFRAN SYSTEMES D'ATTERRISSAGE CANADA INC. (Canada)
Inventeur(s)
Schmidt, R. Kyle
Sinclair, Michael
Chan, Edward Chun Kei
Abrégé
An uplock assembly for retaining and releasing landing gear systems, said uplock assembly comprising: a thermal actuator comprising: a chamber configured to contain expansible material therein; a heating mechanism coupled to said chamber for heating said expansible material and causing volumetric expansion thereof; a piston slidably coupled to said chamber and adapted to extend in response to said volumetric expansion; and an uplock release mechanism releasably engaged by said piston when extended such that said engaged uplock release mechanism causes the release of said landing gear.
SAFRAN LANDING SYSTEMS CANADA INC. / SAFRAN SYSTEMES D'ATTERRISSAGE CANADA INC. (Canada)
Inventeur(s)
Brookfield, Chris
Abrégé
The present invention provides an aircraft landing bay door mechanism that includes the use of a roller slot mechanism for opening and closing the landing bay door.
SAFRAN LANDING SYSTEMS CANADA INC./SAFRAN SYSTEMES D'ATTERRISSAGE CANADA INC. (Canada)
Inventeur(s)
Brookfield, Chris
Abrégé
The present invention provides an aircraft landing bay door mechanism that includes the use of a roller slot mechanism for opening and closing the landing bay door.
brevets
