A multi-zone anti-icing system for an aircraft part. The system includes at least two or more-part zones configured with the aircraft part and an electrothermal heater associated with at least one part zone of the aircraft part; at least one resistive temperature detector (RTD) associated with each part zone of the aircraft part configured to generate temperature data associated with each part zone. A controller coupled to the electrothermal heater and configured to implement an algorithm of a control logic for an anti-icing operation that uses feedback temperature data from at least one RTD at an associated part zone wherein the feedback temperature data is analyzed by the controller via the algorithm to assess reliability of the temperature data generated by the at least one RTD associated with each part zone.
B64D 15/22 - Mise en action automatique par détecteur de givrage
B64D 15/12 - Dégivrage ou antigivre des surfaces externes des aéronefs par chauffage électrique
B64D 33/02 - Aménagement sur les aéronefs des éléments ou des auxiliaires des ensembles fonctionnels de propulsion, non prévu ailleurs des entrées d'air de combustion
2.
HEATER DESIGN FOR CARBON ALLOTROPE ICE PROTECTION SYSTEMS
An ice protection system for an aircraft component includes a plurality of heaters. The aircraft component has at least two section and a junction area. At least one of the heaters is an H-shape carbon allotrope heater designed to apply heat to the junction area and prevent ice accumulation in the junction area.
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
A device for extracting a deeply embedded helical coil is provided. The device includes a shaft, the shaft comprising a proximal end and a distal end; and a blade coupled to the distal end of the shaft, wherein the blade is configured to traverse into a mounting hole to engage the deeply embedded helical coil free of contact with a side of the mounting hole and wherein the deeply embedded helical coil is at least three to five thread pitches below a surface of the mounting hole.
B25B 27/30 - Outils à main ou outillage d'établi, spécialement conçus pour assembler ou séparer des pièces ou des objets, que cela entraîne ou non une certaine déformation, non prévus ailleurs pour assembler des objets autrement que par ajustage à la presse, ou pour les détacher pour mettre en place ou extraire des ressorts, p.ex. des ressorts hélicoïdaux ou à lame
4.
ADDITIONAL SAFETY FEATURE IN AIRCRAFT BRAKING SYSTEM
A method for braking an aircraft is disclosed herein. The method includes receiving, by a brake controller, a first signal from a position sensor of a first pedal, receiving, by the brake controller, a second signal from a pedal sensor of the first pedal, determining, by the brake controller, that the pedal is being pressed based on the first and second signals, and sending, by the brake controller, an instruction to apply a brake pressure in response to the determination that the pedal is being pressed.
B64F 5/10 - Fabrication ou assemblage d’aéronefs, p.ex. gabarits à cet effet
5.
EXTERIOR AIRCRAFT LIGHT WITH INTEGRATED LIGHT OUTPUT MONITORING, AIRCRAFT COMPRISING SUCH EXTERIOR AIRCRAFT LIGHT, AND METHOD FOR MONITORING A LIGHT OUTPUT OF AN EXTERIOR AIRCRAFT LIGHT
Goodrich Lighting Systems GmbH & Co. KG (Allemagne)
Inventeur(s)
Jha, Anil Kumar
Hessling-Von Heimendahl, Andre
Depta, Marion
Abrégé
An exterior aircraft light with integrated light output monitoring includes a light source support, at least one light source, arranged on an outward facing side of the light source support, an aperture in the light source support, a light collection surface, arranged to direct an output monitoring light portion of the light, emitted by the at least one light source, through the aperture in a predefined angular range with respect to the light source support. The light also includes a light detector, arranged on a back side of the light source support, and a total internal reflection optical element, arranged to direct the output monitoring light portion, having travelled through the aperture in the predefined angular range with respect to the light source support, to the light detector via total internal reflection.
B64D 47/06 - Aménagements ou adaptations des dispositifs de signalisation ou d'éclairage pour signaler la présence de l'aéronef
B64D 47/04 - Aménagements ou adaptations des dispositifs de signalisation ou d'éclairage les dispositifs d'éclairage étant essentiellement destinés à éclairer la route sur l'avant
H05B 47/11 - Commande de la source lumineuse en réponse à des paramètres détectés en détectant la luminosité ou la température de couleur de la lumière ambiante
6.
AIRCRAFT READING LIGHT, AIRCRAFT COMPRISING AN AIRCRAFT READING LIGHT, AND METHOD OF OPERATING AN AIRCRAFT READING LIGHT
Goodrich Lighting Systems GmbH & Co. KG (Allemagne)
Inventeur(s)
Jha, Anil Kumar
Hessling-Von Heimendahl, Andre
Pawliczek, Carsten
Leuschner, Jens
Abrégé
An aircraft reading light with a color-tunable reading light output includes: a white light source for emitting white light; a colored light source for emitting colored light; and an optical element, which is arranged for directing colored light that is emitted by the colored light source onto the white light source for being diffusely reflected at the white light source. The colored light source is controllable independently from the white light source.
A method of forming a metallic coating a workpiece is disclosed herein. The method includes receiving a sacrificial deposition rod formed of a first material, receiving a workpiece of a second material, forming a coating of the first material from the sacrificial deposition rod onto the workpiece, the coating having a first thickness, and machining the coating to a second thickness that is less than the first thickness.
A composite drive shaft includes a web-based body defining a longitudinal axis. The web-based body has a first composite layup end section, a second composite layup end section that is opposite to the first composite layup end section, a first spiral composite element extending between the first composite end section and the second composite layup end section, and a second spiral composite element extending between the first composite end section and the second composite layup end section. The first spiral composite element and the second composite spiral element are embedded into the first composite layup end section, and the second composite layup end section. The first composite spiral element and the second composite spiral element are arranged in a bi-directional orientation relative to the longitudinal axis. The first spiral composite element and the second spiral composite element are arranged at pre-determined angles and possess a uni-directional fiber-reinforced polymer-matrix composite structure.
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.
A testing device includes a first member to be positioned on one surface of a part to be tested. A second member to be positioned on an opposed surface of the part to be tested. One of the first and second members have an ultrasonic transmitter and the other has an ultrasonic receiver. At least one of the first and second members have at least one magnetic element and the other of the first and second member have at least one magnetic or at least one ferromagnetic metallic element such that when one of the first and second members moves along the surface of the tested part the other of the first and second members will move along an opposed surface with the one of the members.
A method of testing a part includes placing a first member on a part to be tested. A second member is placed on an opposed surface of the part. One of the members has an ultrasonic transmitter and the other has an ultrasonic receiver. At least one of the members has at least one magnetic element and the other has at least one of a magnetic element or a ferromagnetic metallic element which is attracted to magnets. One of the members moves along the surface of the part such that magnetic attraction causes the other to move along the opposed surface of the part with the one of the members. A controller causes an ultrasonic signal to be sent from the transmitter through the part to be tested which is received by the receiver and then analyzed by an ultrasonic testing machine.
G01N 29/22 - Recherche ou analyse des matériaux par l'emploi d'ondes ultrasonores, sonores ou infrasonores; Visualisation de l'intérieur d'objets par transmission d'ondes ultrasonores ou sonores à travers l'objet - Détails
12.
TRANSLATING SECTIONS OF AN ICING WIND TUNNEL TO EXPAND WATER DROPLET SIZE RANGE
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.
A heating arrangement for a valve includes a thermally conductive heating wire embedded within a body of the valve. Also provided is a valve body formed by additive manufacture and having a thermally conductive heating wire embedded therein to which electric power is applied to cause the thermally conductive heating wire to generate heat in the valve body. A method of manufacture is also provided.
A flexible diaphragm coupler includes a flange having a central support and a flange element extending radially outwardly from the central support. The flange element includes a rim portion having an axially facing surface. The axially facing surface includes a plurality of interlock elements. A diaphragm member is disposed between the first flange and the second flange. The diaphragm member includes a diaphragm element. The diaphragm element includes a central support element and a disc member extending radially outwardly from the central support element. The disc member includes a rim element having an axially facing surface portion including a plurality of interlock members that connect with the plurality of interlock elements.
B64D 35/08 - Transmission de la puissance du groupe moteur aux hélices ou aux rotors; Aménagements des transmissions caractérisée par le fait que la transmission est entraînée par plusieurs groupes moteurs
F16D 1/02 - 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
F16D 3/16 - Joints universels dans lesquels la flexibilité est réalisée par pivots ou organes de liaisons coulissants ou roulants
15.
AIRCRAFT BEACON LIGHT, AIRCRAFT WITH AN AIRCRAFT BEACON LIGHT AND METHOD OF OPERATING AN AIRCRAFT BEACON LIGHT
Goodrich Lighting Systems GmbH & Co. KG (Allemagne)
Inventeur(s)
Depta, Marion
Jha, Anil Kumar
Hessling-Von Heimendahl, Andre
Leuschner, Jens
Abrégé
An aircraft beacon light includes a plurality of primary light sources for emitting light into at least two spatial sectors, wherein the at least two spatial sectors include a forward sector and at least one of an aft sector, a starboard lateral sector, and a portside lateral sector; and a light transmissive cover, which covers the plurality of primary light sources. The plurality of primary light sources are arranged and configured for providing an FAR-compliant aircraft beacon light output of the aircraft beacon light, in case of the light transmissive cover being in a non-eroded state. The aircraft beacon light also includes at least one booster light source for selectively emitting a booster light output into the forward sector. The at least one booster light source is controllable independently of the plurality of primary light sources.
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.
B05B 12/06 - Aménagements de commande de la distribution; Aménagements de réglage de l’aire de pulvérisation pour la commande de la durée ou de la succession des distributions pour réaliser un écoulement pulsatoire
B05B 12/08 - Aménagements de commande de la distribution; Aménagements de réglage de l’aire de pulvérisation sensibles à l'état du liquide ou d'un autre matériau fluide expulsé, du milieu ambiant ou de la cible
17.
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.
A system for releasing a blowout panel and softcover release of an evacuation slide in an aircraft is provided. The system includes a first actuator, a second actuator; and a controller. The controller is configured to receive an indication that an evacuation event has begun; and, responsive to receiving the indication of the evacuation event beginning: send a first signal to the first actuator that magnetizes a first magnetostriction material within the first actuator, thereby releasing the blowout panel of a packboard compartment in which the evacuation slide is present; and send a second signal to the second actuator that magnetizes a second magnetostriction material within the second actuator, thereby releasing a key-loop of lacing associated with the softcover in which the evacuation slide is present in the packboard compartment.
A system for controlling in-flight services using gestures is disclosed. The system comprises: a gesture detection device; an actuator; and a controller. The controller is configured to: receive a detected free space gesture from the gesture detection device; compare the detected free space gesture to a plurality of identified free space gestures; responsive to identifying a free space gesture from the plurality of identified free space gestures, identify an associated in-flight service based on the identified free space gesture; and responsive to identifying the associated in-flight service, send a first command to the actuator to perform the associated in-flight service.
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 is provided for measuring a thickness of a preform material. The system includes a material detection device and a controller, wherein the controller is configured to: receive, from the material detection device, a signal indicating a presence of the preform material; responsive to receiving the signal, receive a first set of measurements along at least a portion of a length of the preform material; convert the first set of measurements into a second set of measurements; and record the second set of measurements.
G01B 17/02 - Dispositions pour la mesure caractérisées par l'utilisation de vibrations infrasonores, sonores ou ultrasonores pour mesurer l'épaisseur
G01N 21/25 - Couleur; Propriétés spectrales, c. à d. comparaison de l'effet du matériau sur la lumière pour plusieurs longueurs d'ondes ou plusieurs bandes de longueurs d'ondes différentes
A system for controlling tension on textile material used in forming a preform is disclosed herein. The system includes a sensor and a controller, where the controller is configured to: receive a signal, from the sensor, indicative of a compressive force applied by the textile material feeding into the system; determine whether the compressive force is within range of a setpoint of the tension for the textile material; and responsive to the compressive force being outside the range, send a command of at least one of an increase or a decrease of the tension on the textile material.
A brake system and method of braking for an aircraft are provided. The brake system includes a primary brake control unit and an alternate brake control unit. In response to the primary brake control unit being placed in an active mode, the primary brake control unit is configured to send data on a set of channels to control brake operation of at least one brake, while the alternate brake control unit is configured to monitor brake temperature on another, separate set of channels coupled to at least one brake temperature sensor associated with the at least one brake.
B60T 8/88 - 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 des moyens sensibles au fonctionnement défectueux, c. à d. des moyens pour détecter et indiquer un fonctionnement défectueux des moyens sensibles à la condition de vitesse
B60T 8/17 - Utilisation de moyens de régulation électriques ou électroniques pour la commande du freinage
B60T 8/171 - Détection des paramètres utilisés pour la régulation; Mesure des valeurs utilisées pour la régulation
B60T 8/92 - 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 des moyens sensibles au fonctionnement défectueux, c. à d. des moyens pour détecter et indiquer un fonctionnement défectueux des moyens sensibles à la condition de vitesse à action corrective automatique
24.
EXTERIOR AIRCRAFT LIGHT, AIRCRAFT COMPRISING AN EXTERIOR AIRCRAFT LIGHT, AND METHOD FOR PROVIDING AN EXTENT OF EROSION OF AN EXTERIOR SURFACE OF A LIGHT TRANSMISSIVE COVER OF AN EXTERIOR AIRCRAFT LIGHT
Goodrich Lighting Systems GmbH & Co. KG (Allemagne)
Inventeur(s)
Hessling-Von Heimendahl, Andre
Depta, Marion
Abrégé
An exterior aircraft light includes a support and a light transmissive cover having a light transmissive body with an interior surface and an exterior surface. The light includes at least one light source arranged between the support and the light transmissive cover; and a first light detector. The light transmissive cover has a first light guide path within the light transmissive body from a first light entry region to a first light exit region, wherein the first light detector is arranged to receive light that travels along the first light guide path and that exits the light transmissive cover at the first light exit region. The first light detector is configured to provide sensor measurements corresponding to the amount of light incident on the first light detector.
B64D 47/02 - Aménagements ou adaptations des dispositifs de signalisation ou d'éclairage
G01N 21/25 - Couleur; Propriétés spectrales, c. à d. comparaison de l'effet du matériau sur la lumière pour plusieurs longueurs d'ondes ou plusieurs bandes de longueurs d'ondes différentes
B64D 45/00 - Indicateurs ou dispositifs de protection d'aéronefs, non prévus ailleurs
25.
PROTECTIVE COVER FOR A FUSELAGE-MOUNTED EXTERIOR AIRCRAFT LIGHT AND EXTERIOR AIRCRAFT LIGHT
Goodrich Lighting Systems GmbH & Co. KG (Allemagne)
Inventeur(s)
Jha, Anil Kumar
Hessling-Von Heimendahl, Andre
Schön, Christian
Tsibadze, Christo
Abrégé
A protective cover for a fuselage-mounted exterior aircraft light includes a fuselage-facing mounting side for mounting the protective cover to an exterior aircraft light housing or to an exterior skin of an aircraft; a light transmissive forward facing light emission surface; and an air deflection zone, which is shaped to direct a portion of an impinging air stream (A) along and over the forward facing light emission surface for shielding the forward facing light emission surface from the impinging air stream (A).
A heat shield panel comprising an inner heat shield layer and an outer heat shield layer, the inner heat shield layer and the outer heat shield layer each having two outer edges wherein the outer edges of the inner heat shield layer and the outer edges of the inner heat shield layer are substantially aligned and are affixed to each other to form heat shield panel edges, and wherein the inner heat shield layer is formed of two or more segments each having an inner edge, the inner edges of the segments being arranged to move relative to each other.
A portable container for being loaded into and unloaded from a compartment of an aircraft, the portable container comprises a power source comprising one or more rechargeable batteries and coupling circuitry configured to electrically couple one or more of the rechargeable batteries to an electrical connector, and a housing comprising the power source, wherein the power source is operable to discharge one or more of the rechargeable batteries and transmit a discharge current via the electrical connector, and wherein the electrical connector comprises an interface portion operable to be physically connectable with a corresponding interface portion of another electrical connector to electrically couple the electrical connector to the another electrical connector.
A rinse device has a housing part and a rinse head. The rinse head has a plurality of openings through which the pressurised fluid is ejected. The housing part includes an outer housing tube and an inner piston movable axially relative to the outer housing tube, and a sealed air-filled cavity defined therebetween, and a spring attached at a first end to the outer housing tube and at a second end to the piston, and wherein the rinse head is attached to the piston at the second end of the housing part, such that the spring is biased to hold the piston at a first axial position relative to the outer housing tube until a force exerted by the pressure of the fluid inside the housing part exceeds the sum of an axial force of the spring and the force from the pressure of the air in the air cavity.
A torque plate barrel for use with a brake system is disclosed herein. The torque plate barrel includes a barrel body having an outer diameter, an inner diameter, and an axial length extending from a first end to an opposing second end, wherein the inner diameter varies along the axial length and the outer diameter is fixed along the axial length.
A method of fabricating a composite component, includes forming a fibrous preform by forming a first ceramic particle layer over a first textile layer, the first ceramic particle layer having a first group of ceramic particles, disposing a second textile layer over the first ceramic particle layer, forming a second ceramic particle layer over the second textile layer, the second ceramic particle layer having a second group of ceramic particles, and disposing a third textile layer over the second ceramic particle layer. The method further includes densifying the fibrous preform.
C04B 35/622 - Procédés de mise en forme; Traitement de poudres de composés inorganiques préalablement à la fabrication de produits céramiques
C04B 35/563 - Produits céramiques mis en forme, caractérisés par leur composition; Compositions céramiques; Traitement de poudres de composés inorganiques préalablement à la fabrication de produits céramiques à base de non oxydes à base de carbures à base de carbure de bore
C04B 41/50 - Revêtement ou imprégnation avec des substances inorganiques
C04B 35/83 - Fibres de carbone dans une matrice carbonée
C04B 41/91 - Post-traitement des mortiers, du béton, de la pierre artificielle ou des céramiques; Traitement de la pierre naturelle de céramiques uniquement impliquant l'enlèvement d'une partie des matières des objets traités, p.ex. par attaque chimique
31.
SOLENOID/MAGNETIC HOLD BRAKE WITH POWER OFF MAGNET HOLD FUNCTION
A power drive unit (PDU) having a magnetic hold brake for use in an aircraft is disclosed herein. The PDU includes a wheel configured to convey cargo through a portion of the aircraft, a motor coupled to the wheel, a brake disk, a solenoid configured to apply a first force to move the brake disk in a first direction to resist rotation of the motor, wherein the solenoid is further configured to apply a second force to move the brake disk in a second direction opposite the first direction to allow the motor to rotate, and a magnet configured to apply a third force to the brake disk, the third force being in the first direction to apply a drag force to the motor.
B64D 9/00 - Appareillage pour manutention du fret; Appareillage pour faciliter l'embarquement des passagers ou autres
F16D 55/02 - Freins à surfaces de freinage substantiellement radiales pressées l'une contre l'autre dans une direction axiale, p.ex. freins à disques avec disques ou patins déplaçables selon l'axe pressés contre des organes en rotation situés dans l'axe
F16D 63/00 - Freins non prévus ailleurs; Freins combinant plusieurs des types mentionnés dans les groupes
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
B65G 13/02 - Chemins de roulement comportant des rouleaux entraînés
A piston assembly for engaging two selectively engageable parts comprising: a housing defining a piston cylinder; a piston; and an adjuster assembly comprising: a piston stroke limiter configured to limit the length of a return stroke of the piston from an extended stroke position and a retracted stroke position, the piston stroke limiter comprising a spring and a spring guide; and a crushable body, acting between the piston and the piston stroke limiter, the crushable body being arranged to reduce in axial length when a length of an extension stroke exceeds a length of a retraction stroke to maintain the length of the return stroke; wherein the crushable body comprises an inner crushable thin-walled tube surrounding at least a portion of the piston and an outer crushable thin-walled tube mounted around and radially outwards of the inner crushable tube.
F16D 65/54 - Dispositifs de réglage mécaniques agissant automatiquement dans une direction pour le réglage d'un jeu excessif par réglage linéaire direct
A hybrid water storage system for an aircraft includes separate variable volumes for respectively storing/holding potable water and gray water occupying a common container. The hybrid water storage system is generally configured to draw potable water from a first variable volume in order to provide fresh water to one or more aircraft appliances (e.g., sinks, showers, ice-makers, etc.), and the used potable water (i.e., the potable water that is collected in drains from the aircraft appliances), referred to herein as gray water, is routed to a second variable volume that occupies the same container as the first variable volume.
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 first structural element and a second material composition of at least one of a second structural element. The first material composition may comprise an alpha-beta titanium alloy. The second material composition may comprise a beta titanium alloy.
B23K 35/02 - Baguettes, électrodes, matériaux ou environnements utilisés pour le brasage, le soudage ou le découpage caractérisés par des propriétés mécaniques, p.ex. par la forme
B22F 3/24 - Traitement ultérieur des pièces ou objets
B22F 10/64 - Traitement de pièces ou d'articles après leur formation par des moyens thermiques
A pixel system for an imaging device can include one or more pixels comprising a pulse trigger assembly configured to detect a pulse at one or more threshold voltages, a timer system forming part of and/or connected to the one or more pixels, the timer system comprising one or more trigger switches. The pulse trigger assembly can be configured to activate the one or more trigger switches in response to detecting the pulse at the one or more threshold values. The pixel system can include a time-of-flight (TOF) module operatively connected to the one or more pixels and/or the timer system to determine a TOF based on an output from the timer system while simultaneously performing either or both passive imaging and asynchronous laser pulse detection.
G01S 7/487 - Extraction des signaux d'écho désirés
G01S 7/4861 - Circuits pour la détection, d'échantillonnage, d'intégration ou de lecture des circuits
G01S 7/4865 - Mesure du temps de retard, p.ex. mesure du temps de vol ou de l'heure d'arrivée ou détermination de la position exacte d'un pic
G01S 17/10 - Systèmes déterminant les données relatives à la position d'une cible pour mesurer la distance uniquement utilisant la transmission d'ondes à modulation d'impulsion interrompues
G01S 17/89 - Systèmes lidar, spécialement adaptés pour des applications spécifiques pour la cartographie ou l'imagerie
36.
Magneto Strictive Actuated Pressure Regulator Module For Inflation System
An actuator is disclosed herein. The actuator includes a drive body including a bottom surface, the bottom surface having a first side and an opposing second side, a magneto strictive material disposed within the drive body and contacting the first side of the bottom surface of the drive body, a solenoid disposed within the drive body and surrounding the magneto strictive material, a drive rod extending through the magneto strictive material and through the bottom surface of the drive body, and a spring disposed adjacent the second side of the bottom surface of the drive body, wherein the drive rod extends through the spring.
F16K 17/16 - Soupapes ou clapets de sûreté; Soupapes ou clapets d'équilibrage fermant sur insuffisance de pression d'un côté avec élément de rupture l'élément étant un diaphragme de rupture
A system for displaying an artificial horizon in an enclosed space. The system includes a first plurality of visual effect sources located in the enclosed space and configured to generate a first visual effect of the artificial horizon consistent with an orientation detected by an orientation sensor. The system further includes a second plurality of visual effect sources separate from the first plurality of visual effect sources and located in the enclosed space and configured to generate a second visual effect of the artificial horizon different from the first visual effect consistent with the orientation detected by the orientation sensor.
A wheel assembly is disclosed herein. The wheel assembly includes a torque bar extending in a first direction, a retainer plate coupled to the torque bar, the retainer plate having a first side formed into a first U-channel, the first U-channel formed in a second direction perpendicular to the first direction, a heat shield panel having a first side formed into a second U-channel, the second U-channel of the heat shield panel being formed in a third direction opposite the second direction, and a retention clasp formed from a portion of the heat shield panel, the retention clasp formed over an open end of the second U-channel.
A device for extracting a deeply embedded helical coil is provided. The device includes a shaft, the shaft comprising a proximal end and a distal end; and a blade coupled to the distal end of the shaft, wherein the blade is configured to traverse into a mounting hole to engage the deeply embedded helical coil free of contact with a side of the mounting hole and wherein the deeply embedded helical coil is at least three to five thread pitches below a surface of the mounting hole.
B23P 11/00 - Assemblage ou désassemblage de pièces ou d'objets métalliques par des processus du travail du métal non prévus ailleurs
B25B 27/30 - Outils à main ou outillage d'établi, spécialement conçus pour assembler ou séparer des pièces ou des objets, que cela entraîne ou non une certaine déformation, non prévus ailleurs pour assembler des objets autrement que par ajustage à la presse, ou pour les détacher pour mettre en place ou extraire des ressorts, p.ex. des ressorts hélicoïdaux ou à lame
B64C 25/36 - Aménagements ou adaptations des roues, des pneumatiques ou des essieux
40.
LIGHT MODULE FOR AN ELONGATED INTERIOR AIRCRAFT LIGHT, ELONGATED INTERIOR AIRCRAFT LIGHT, AND METHOD OF ASSEMBLING AN ELONGATED INTERIOR AIRCRAFT LIGHT
Goodrich Lighting Systems GmbH & Co. KG (Allemagne)
Inventeur(s)
Pawliczek, Carsten
Hessling-Von Heimendahl, Andre
Abrégé
A light module for an elongated interior aircraft light comprises a plurality of light sources, which are configured for emitting light of different colors and which are arranged next to each other, forming an array of light sources extending between a first end and a second end along a longitudinal direction (LD). The plurality of light sources include a first light source, which is arranged at the first end, and a second light source, which is arranged at the second end. The first and second light sources are those from the plurality of light sources that result in a difference of the illuminating properties between the first and second light sources being the smallest difference that is possible for all potential pairs of light sources formed from the plurality of light sources.
B64D 11/00 - Arrangements pour passagers ou équipage; Installations de postes de pilotage non prévues ailleurs
F21S 4/28 - Dispositifs ou systèmes d'éclairage utilisant une guirlande ou une bande de sources lumineuses avec les sources lumineuses maintenues par ou à l'intérieur de supports allongés rigides, p.ex. barres à LED
41.
AIRCRAFT BEACON LIGHT, AIRCRAFT COMPRISING AN AIRCRAFT BEACON LIGHT, AND METHOD OF DETERMINING A HEALTH STATUS OF AN AIRCRAFT BEACON LIGHT
Goodrich Lighting Systems GmbH & Co. KG (Allemagne)
Inventeur(s)
Hessling-Von Heimendahl, Andre
Schallenberg, Björn
Abrégé
An aircraft beacon light comprises an annular light source support having a plurality of light passing portions; a plurality of light sources, arranged on the annular light source support for a radially outwards emission of light flashes; a light detector for sensing a light output level of at least a subset of the plurality of light sources; and at least one optical element for shaping a beacon light output from light emitted by the plurality of light sources, the at least one optical element having at least one light guiding portion for capturing stray light from at least said subset of the plurality of light sources and for guiding said stray light through the plurality of light passing portions and towards the light detector.
B64D 47/04 - Aménagements ou adaptations des dispositifs de signalisation ou d'éclairage les dispositifs d'éclairage étant essentiellement destinés à éclairer la route sur l'avant
F21V 23/04 - Agencement des éléments du circuit électrique dans ou sur les dispositifs d’éclairage les éléments étant des interrupteurs
F21V 5/04 - Réfracteurs pour sources lumineuses de forme lenticulaire
B64D 45/00 - Indicateurs ou dispositifs de protection d'aéronefs, non prévus ailleurs
A method includes imaging a first graybody with a focal plane array (FPA), wherein the first graybody has a first emissivity, and imaging a second graybody having a lower emissivity than the first graybody. The method includes using data captured while imaging the first and 5 second graybodies to perform non-uniformity correction (NUC) of the FPA.
A piston assembly is disclosed herein. The piston assembly includes a piston having a first end, an opposing second end, and a sidewall extending from the first end to the second end, the piston further including a cavity at least partially defined by the sidewall, a spring guide having a first end and an opposing second end, the spring guide disposed within the cavity of the piston and adjacent the sidewall, an insulator having a first portion extending from the second end of the piston and a second portion disposed within the piston, an insulator shield disposed adjacent the first portion of the insulator, and a component coupled to the second end of the spring guide, the component being offset from the insulator shield by a distance.
F16D 65/84 - Caractéristiques relatives au refroidissement pour freins à disques
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
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 friction disk may comprise a first wear surface formed from a carbon fiber-carbon matrix composite material. A wear plug may be located in an opening defined by the carbon fiber-carbon matrix composite material. The wear plug may extend axially from the wear surface. The wear plug may comprise a rod or a particulate.
F16D 65/12 - Disques; Tambours pour freins à disques
B29C 70/54 - 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 opération de façonnage des matières composites comprenant uniquement des renforcements - Parties constitutives, détails ou accessoires; Opérations auxiliaires
B29C 70/68 - 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 en incorporant ou en surmoulant des parties préformées, p.ex. des inserts ou des couches
A method of controlling an aircraft braking system includes initiating the aircraft braking system by receiving a first brake command at a primary system to actuate braking via the primary system, receiving the first brake command at an alternate system, and in response to the primary system losing an ability to control a brake, controlling the braking of the brake via the alternate system.
B60T 8/94 - 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 des moyens sensibles au fonctionnement défectueux, c. à d. des moyens pour détecter et indiquer un fonctionnement défectueux des moyens sensibles à la condition de vitesse à action corrective automatique sur un régulateur de pression fluidique
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 heat shield for a wheel assembly may comprise a plurality of heat shield segments, a plurality of shield bumpers may be coupled to a radially outward surface of each heat shield segment, and a plurality of heat shield retainers coupled to the plurality of heat shield segments. Each heat shield retainer may include a first bumper standoff and a second bumper standoff located over a first radially outward surface of the heat shield retainer. Each of the first bumper standoff and the second bumper standoff may comprise an attachment portion coupled to the first radially outward surface of the heat shield retainer and a bumper portion defining a bumper opening.
An aircraft braking system is disclosed that includes a first pedal, first and second pedal sensors for the first pedal, a first brake control unit (e.g., primary), and a separate second brake control unit (e.g., secondary). The first pedal position sensor is operatively interconnected with one of the first brake control unit and the second brake control unit, while the second pedal position sensor is operatively interconnected with the other of the first brake control unit and the second brake control unit. Outputs from these pedal sensors may be used to control operation of the aircraft braking system in at least some fashion.
A clip assembly for a rotor disk of a brake assembly, the clip assembly comprising: a half-cap clip arranged to fit over an end of a lug of the rotor disk, the half-cap clip having two opposing sides and an end across the two opposing sides, and a top and bottom surface, the top and bottom surfaces, the sides and the end defining a receptacle to receive the rotor lug, the half-cap clip having an aperture in each of the sides; and a pin having a pin head and a pin body extending from the pin head along an axis (A) of the pin, the pin having a cross-section defining an elongate shape having rounded ends; and wherein the apertures in the sides of the half-cap clip are shaped to receive the pin body.
A retainer for connecting two panels of a heat shield assembly, the retainer comprising: a central elongate panel having a length l and a width w, a top end, a bottom end and first and second long sides extending from the top end to the bottom end; a first side panel extending along the first long side of the central elongate panel and a second side panel extending along the second long side of the central elongate panel; and wherein reinforcement features are applied to a surface of the central elongate panel.
A seal plate disposable between a pair of preforms for chemical vapor infiltration is disclosed. The seal plate may include a plurality of first channels that extend completely through the seal plate and that are located between an inner annulus and outer annulus of the seal plate. The seal plate may further include a plurality of second channels that also extend completely through the seal plate and that are located also between an inner annulus and outer annulus. The first channels may differ from the second channels in at least one respect (e.g., the first channels may be of a different width than the second channels). The first channels may provide an inlet for the chemical vapor infiltration of the preform, while the second channels may provide an outlet for the chemical vapor infiltration of the preform.
A method for forming an oxidation protection system on a composite structure may comprise applying a ceramic layer slurry to the composite structure and heating the composite structure to form a ceramic layer on the composite structure. The ceramic layer slurry may comprise aluminum and silicon carbide powder in a sol. The ceramic layer may comprise alumina, silicon carbide and silicon oxycarbide.
C04B 35/622 - Procédés de mise en forme; Traitement de poudres de composés inorganiques préalablement à la fabrication de produits céramiques
C04B 35/565 - Produits céramiques mis en forme, caractérisés par leur composition; Compositions céramiques; Traitement de poudres de composés inorganiques préalablement à la fabrication de produits céramiques à base de non oxydes à base de carbures à base de carbure de silicium
C04B 41/50 - Revêtement ou imprégnation avec des substances inorganiques
A bidirectional latching device for securing a cargo in a vehicle may have a latch catch assembly and a latch head. The latch catch assembly may selectably engage with the latch head. When engaged with the latch head, the latch catch assembly may lock the latch head in position to resist movement and the latch head may secure the cargo in the vehicle. When disengaged from the latch head, the latch catch assembly may release the latch head and the latch head may move to a stowed position. The latch catch assembly may lock the latch head to resist movement in one or more directions of movement. The latch head may be shaped to secure the cargo in the vehicle in at least two directions. Thus, cargo may be secured more efficiently by requiring a reduced number of latch devices because the disclosed latch device is bidirectional.
A tray connector is disclosed herein. The tray connector includes a first side rail, a second side rail, parallel to the first side rail, a cross member extending from the first side rail to the second side rail, a pin extending from within the cross member and through the first side rail, and a tab configured to retract the pin.
A method of manufacturing a carbon structure can comprise: infiltrating the carbon structure with a silicon oxycarbide (SiOC) precursor sol; and densifying the carbon structure by chemical vapor infiltration (CVI) to form a carbon and ceramic matrix composite material, the carbon and ceramic matrix composite material comprising between 0% and 15% by weight of a plurality of ceramic particles from the ceramic compound, densifying the carbon structure including adjusting a temperature gradient across the carbon structure.
C04B 35/56 - Produits céramiques mis en forme, caractérisés par leur composition; Compositions céramiques; Traitement de poudres de composés inorganiques préalablement à la fabrication de produits céramiques à base de non oxydes à base de carbures
C04B 35/52 - Produits céramiques mis en forme, caractérisés par leur composition; Compositions céramiques; Traitement de poudres de composés inorganiques préalablement à la fabrication de produits céramiques à base de non oxydes à base de carbone, p.ex. graphite
57.
IN-SITU SILICON OXYCARBIDE FORMATION IN CARBON-CARBON COMPOSITES
A method of making a carbon-carbon composite may comprise forming a silicon oxycarbide (SiOC) precursor sol and infiltrating a fibrous preform with the SiOC precursor sol. A SiOC forming heating treatment may be performed on the fibrous preform to form SiOC particles. The fibrous preform may be densified using chemical vapor infiltration to form a densified fibrous preform.
C04B 35/56 - Produits céramiques mis en forme, caractérisés par leur composition; Compositions céramiques; Traitement de poudres de composés inorganiques préalablement à la fabrication de produits céramiques à base de non oxydes à base de carbures
C04B 35/52 - Produits céramiques mis en forme, caractérisés par leur composition; Compositions céramiques; Traitement de poudres de composés inorganiques préalablement à la fabrication de produits céramiques à base de non oxydes à base de carbone, p.ex. graphite
58.
SYSTEMS AND METHODS FOR AIR CARGO CONTAINER DAMAGE MONITORING
A method of monitoring cargo loading by an aircraft field device may be used to detect damage to cargo and ULDs, reducing the need for manual inspection of the cargo and/or eliminate the need for constant human monitoring of cargo loading. The method may comprise scanning ULDs and receiving image data of the ULDs, and sending the data to an on ground infrastructure network. The on ground infrastructure network may classify ULD type and classify damage to the ULDs. The damage classification may be received by the field device. The field device may generate an alert and/or halt cargo loading in response to the damage classification.
An aircraft light unit is disclosed herein. The aircraft light unit includes a housing having a first side and an opposing second side, a light coupled to the first side of the housing, a circuit board assembly coupled to second side of the housing, a thermoelectric cooler coupled to the circuit board assembly and configured to dissipated heat from the circuit board assembly, and a heat sink disposed over the thermoelectric cooler and configured to dissipate heat from the thermoelectric cooler.
F21S 45/47 - Refroidissement passif, p.ex. en utilisant des ailettes, des éléments thermiquement conducteurs ou des ouvertures
F21V 29/54 - Dispositions de refroidissement utilisant des moyens thermo-électriques, p.ex. des éléments Peltier
G05B 19/4155 - Commande numérique (CN), c.à d. machines fonctionnant automatiquement, en particulier machines-outils, p.ex. dans un milieu de fabrication industriel, afin d'effectuer un positionnement, un mouvement ou des actions coordonnées au moyen de données d'u caractérisée par le déroulement du programme, c.à d. le déroulement d'un programme de pièce ou le déroulement d'une fonction machine, p.ex. choix d'un programme
B64D 47/06 - Aménagements ou adaptations des dispositifs de signalisation ou d'éclairage pour signaler la présence de l'aéronef
60.
AIRCRAFT PASSENGER SERVICE UNIT, AIRCRAFT PASSENGER SERVICE UNIT ASSEMBLY, AND METHOD OF DETERMINING SPATIAL POSITIONS AND/OR ORIENTATIONS OF A PLURALITY OF AIRCRAFT PASSENGER SERVICE UNITS
Goodrich Lighting Systems GmbH & Co. KG (Allemagne)
Inventeur(s)
Ueberschaer, Andreas
Hessling-Von Heimendahl, Andre
Pawliczek, Carsten
Depta, Marion
Abrégé
An aircraft passenger service unit, which is configured for being installed in a passenger cabin of an aircraft. The unit includes at least two near field communication interfaces, wherein each of the at least two near field communication interfaces is configured for a wireless exchange of messages with a corresponding near field communication interface of a neighboring aircraft passenger service unit. The messages include information that identifies the aircraft passenger service unit and the near field communication interface sending the respective message.
H04B 5/00 - Systèmes de transmission à induction directe, p.ex. du type à boucle inductive
B64D 11/00 - Arrangements pour passagers ou équipage; Installations de postes de pilotage non prévues ailleurs
G01S 1/68 - Marqueur, balise d'extrémité, indicatif d'appel ou toutes balises analogues transmettant des signaux ne portant pas d'information directionnelle
G01S 1/04 - Radiophares ou systèmes de balisage émettant des signaux ayant une ou des caractéristiques pouvant être détectées par des récepteurs non directionnels et définissant des directions, situations ou lignes de position déterminées par rapport aux émetteu; Récepteurs travaillant avec ces systèmes utilisant les ondes radioélectriques - Détails
G01S 1/70 - Radiophares ou systèmes de balisage émettant des signaux ayant une ou des caractéristiques pouvant être détectées par des récepteurs non directionnels et définissant des directions, situations ou lignes de position déterminées par rapport aux émetteu; Récepteurs travaillant avec ces systèmes utilisant des ondes électromagnétiques autres que les ondes radio
A clip for a rotor disk of a brake assembly, the clip arranged to fit over an end of a lug of the rotor disk, the clip having two opposing sides and an end portion across the two opposing sides, and a top portion, the top portion, the sides and the end portion each having an inner surface and an outer surface, and the inner surface of the top portion, the sides and the end portion together defining a receptacle to receive the rotor lug, in use, the clip having at least one aperture in each of the sides; the clip further comprising a reinforcement member extending from the inner surface of the end portion internal of the receptacle, between the two sides.
A clip for a rotor disk of a brake assembly, the clip formed of sheet metal to fit in a slot between, and to, ends of adjacent rotor lugs around the periphery of the rotor disk, wherein the clip is shaped to have a main body portion that is substantially rectangular in form and shaped and sized to fit, in use, onto an inner peripheral surface defined by the slot between the ends of two adjacent lugs, and to extend across the length of the slot from a first main body portion edge to a second opposite main body portion edge; and wherein the clip further comprises first and second end portions that extend from the respective ends of the main body portion at an angle, wherein each end portion comprises an outwardly protruding section and an end clip portion.
An actuator for opening a hermetically sealed cylinder is disclosed herein. The actuator includes an actuation chamber configured to receive pressurized gas, the actuation chamber at least partially defined by a top wall and a bottom wall, a cutter body disposed within the actuation chamber between the top wall and the bottom wall, the cutter body including a top portion and a bottom portion, a cutting edge extending from the bottom portion of the cutter body, and a spring disposed between the top portion of the cutter body and the bottom wall of the actuation chamber.
A retainer for connecting two panels of a heat shield assembly, the retainer comprising: a central elongate panel having a length l and a width w, a top end, a bottom end and first and second long sides extending from the top end to the bottom end; a first side panel extending along the first long side of the central elongate panel and a second side panel extending along the second long side of the central elongate panel; a first U-shaped fold joining the central elongate panel first long side to the first side panel, and a second U-shaped fold joining the second long side to the second side panel.
B60B 21/12 - Parties annexes, p.ex. bandes de garniture intérieure
B60B 7/04 - Chapeaux de roue, couronnes ou dispositifs similaires pour orner, protéger ou cacher, entièrement ou en partie, le corps de la roue, la jante, le moyeu ou le flanc du pneumatique constitués de plusieurs parties principales
A clip assembly for a rotor disk of a brake assembly, the clip assembly comprising: a clip formed of sheet metal to fit over an end of a lug of the rotor disk, the clip shaped to have a top surface that extends in a first plane from a first side and then transitions, at an opposite, second side, by a first bend into a front surface that extends in a second plane from a third side at the first bend to a fourth side and transitions by a second bend to an under-surface extending in a third plane to a fifth end, the top surface, the first bend, the front surface, the second bend and the under surface together defining a hook configuration such that, in use, the top surface fits over a top surface of the lug onto which it is mounted.
A retainer for connecting two panels of a heat shield assembly, the retainer comprising: a central elongate panel having a length 1 and a width w, a top end, a bottom end and first and second long sides extending from the top end to the bottom end; a first side panel extending along the first long side of the central elongate panel and a second side panel extending along the second long side of the central elongate panel; and wherein the central elongate panel is corrugated, with corrugations running along the length of the central elongate panel from the top end to the bottom end.
A stator disk assembly for a brake assembly is disclosed. The stator disk assembly includes at least a pair lugs with a recess disposed therebetween, along with a separate stator clip that is separately mounted on each lug of this pair. The stator clip are configured such that a spline of a torque plate that is disposed in the recess will contact only the stator disk and not either of the stator clips in at least certain conditions (e.g., during a braking operation; until crushing of the stator disk). For instance, each of the two ends of each stator clip may be recessed back from the adjacent-most sidewall of the lug on which the stator clip is mounted.
A lightbox is disclosed herein, comprising a lower panel, a back panel connected to the lower panel and extending upward from the lower panel, wherein the back panel is coated in a reflective material, an inner lens connected to the lower panel and extending upward from the lower panel, the inner lens being adjacent the back panel, a first cavity at least partially defined by the back panel and the inner lens, an outer lens connected to the lower panel and extending upward from the lower panel, the outer lens being adjacent the inner lens and opposite the back panel, and a first LED adjacent the lower panel and oriented to emit a light away from the lower panel and into the first cavity.
G02F 1/1335 - Association structurelle de cellules avec des dispositifs optiques, p.ex. des polariseurs ou des réflecteurs
F21K 9/68 - Agencements optiques intégrés dans la source lumineuse, p.ex. pour améliorer l’indice de rendu des couleurs ou l’extraction de lumière - Détails des réflecteurs faisant partie de la source lumineuse
F21K 9/69 - Agencements optiques intégrés dans la source lumineuse, p.ex. pour améliorer l’indice de rendu des couleurs ou l’extraction de lumière - Détails des réfracteurs faisant partie de la source lumineuse
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.
F16H 19/08 - 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 oscillant et vice versa
70.
SYSTEMS AND METHODS FOR LANDING GEAR ACTUATION VIA TRUNNION DRIVE
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.
A fluid level sensor assembly includes a tubular housing arranged to be fitted into a fluid flow path of a system between a fluid line an inlet to a valve (1′), wherein the tubular housing defines an axial flow channel extending through the tubular housing from a first end to a second end, along an axis A, for fluid to flow from the fluid line of the system to the valve inlet, the tubular housing further comprising a sensor channel extending from the second end of the flow channel towards the first end substantially parallel to, and in fluid communication with the axial flow channel, wherein the assembly further comprises first and second sensor parts located in the sensor channel that communicate with each other.
G01F 23/263 - Indication ou mesure du niveau des liquides ou des matériaux solides fluents, p.ex. indication en fonction du volume ou indication au moyen d'un signal d'alarme en mesurant des variables physiques autres que les dimensions linéaires, la pression ou le poids, selon le niveau à mesurer, p.ex. par la différence de transfert de chaleur de vapeur ou d'eau en mesurant les variations de capacité ou l'inductance de condensateurs ou de bobines produites par la présence d'un liquide ou d'un matériau solide fluent dans des champs électriques ou électromagnétiques en mesurant les variations de capacité de condensateurs
G01F 15/00 - MESURE DES VOLUMES, DES DÉBITS VOLUMÉTRIQUES, DES DÉBITS MASSIQUES OU DU NIVEAU DES LIQUIDES; COMPTAGE VOLUMÉTRIQUE - Détails des appareils des groupes ou accessoires pour ces derniers, dans la mesure où de tels accessoires ou détails ne sont pas adaptés à ces types particuliers d'appareils, p.ex. pour l'indication à distance
72.
SHORT RANGE DATA TRANSFER IN WIRELESS CARGO APPLICATIONS
A controller is disclosed herein. The controller includes a processor and a memory operatively coupled to the processor. The memory includes instructions stored thereon that, when executed by the processor, cause the processor to receive authentication credentials for controlling a cargo handling system via an access point. The access point uses a short-range wireless communication protocol. The instructions further cause the processor to connect to the cargo handling system via a wireless communication protocol, receive control of the cargo handling system, and send commands to the cargo handling system.
An aircraft brake insulator assembly for a brake mechanism of an aircraft includes a torque barrel assembly and a multi-layer insulator. The torque barrel assembly includes a torque plate and a torque barrel coupled to the torque plate. The multi-layer insulator is configured to be located between a piston housing of the brake mechanism and the torque plate. The multi-layer insulator includes a first insulator layer and a second insulator layer contacting the first insulator layer.
B32B 3/26 - Produits stratifiés caractérisés essentiellement par le fait qu'une des couches comporte des discontinuités ou des rugosités externes ou internes, ou bien qu'une des couches est de forme générale non plane; Produits stratifiés caractérisés essentiellement par des particularismes de forme caractérisés par une couche comportant des cavités ou des vides internes
B32B 7/05 - Liaison entre couches les couches n’étant pas liées sur toute la surface, p. ex. liaison discontinue ou par motifs particuliers
B32B 15/08 - Produits stratifiés composés essentiellement de métal comprenant un métal comme seul composant ou comme composant principal d'une couche adjacente à une autre couche d'une substance spécifique de résine synthétique
B32B 9/04 - Produits stratifiés composés essentiellement d'une substance particulière non couverte par les groupes comprenant une telle substance comme seul composant ou composant principal d'une couche adjacente à une autre couche d'une substance spécifique
B32B 9/00 - Produits stratifiés composés essentiellement d'une substance particulière non couverte par les groupes
A power drive unit for moving cargo relative to a cargo bay of an aircraft is disclosed herein. The power drive unit includes a lift cam coupled to camshaft, a drive wheel coupled to a drive shaft, and an induction motor having a first output shaft and a second output shaft, the first output shaft configured to drive the drive shaft and the second output shaft configured to drive the camshaft.
The present disclosure provides assemblies, systems and characterization methods of welded joints for thermoplastic components. More particularly, the present disclosure provides assemblies, systems and characterization methods of welded joints for thermoplastic components (e.g., thermoplastic-based fiber-reinforced composites) utilizing visualization agents (e.g., pigments and/or fluorescent agents). The present disclosure provides for assemblies, systems and characterization methods of welded joints for thermoplastic components and/or thermoplastic-based composites with enhanced visualization, sufficient for qualitative and quantitative assessment of the welded interconnected areas.
A fiber reinforced composite component may include interleaved textile layers and ceramic particle layers coated with matrix material. The fiber reinforced composite component may be fabricated by forming a fibrous preform and densifying the fibrous preform. The fibrous preform may be fabricated by performing a silicon melt infiltration after the densification process. A plurality of pores defined by the carbon matrix material are infiltrated with a silicon material and the fibrous preform is heated to a melt temperature until a desired percentage (e.g., at least 50%) of the carbon matrix material is converted into silicon carbide or another oxidation resistant material.
A heat shield for a wheel assembly may comprise a plurality of heat shield segments and a plurality of heat shield retainers coupled to the plurality of heat shield segments. A plurality of shield bumpers may be coupled to a radially outward surface of each heat shield segment of the plurality of arcuate heat shield segments. A first retainer bumper may be located over a first radially outward surface of each heat shield retainer of the plurality of heat shield retainers.
A drive shaft for transferring torque including a tubular insert extending along an axis and defining a first layer of the drive shaft including at least one straight portion and at least one undulation, wherein the tubular insert includes a first material having a first deformation temperature, and a polymeric tubular covering defining a second layer of the drive shaft surrounding the tubular insert including a second material having a deformation temperature lower than the deformation temperature of the first material, wherein the covering includes at least one straight portion adjacent to the straight portion of the tubular insert and at least one undulation adjacent to the at least one undulation of the tubular insert.
B32B 27/08 - Produits stratifiés composés essentiellement de résine synthétique comme seul composant ou composant principal d'une couche adjacente à une autre couche d'une substance spécifique d'une résine synthétique d'une sorte différente
Stator clips may be disposed in the recesses of aircraft brake stator disks to increase the lug strength of the stator disk. The clips may interface with the splines of a torque plate and may comprise ridges that reduce contact between the torque plate barrel and the clip, while maintaining the overall integrity of the clip structure. Furthermore, reduced contact may enable a reduction in drag, improving brake performance.
A stator disk assembly for a brake assembly is disclosed. The stator disk assembly includes at least a pair lugs with a recess disposed therebetween, along with a separate stator clip that is separately mounted on each of the lugs. The stator clips are configured such that a spline of a torque plate barrel that is disposed in the recess will contact only the stator disk and not either of the stator clips in at least certain conditions (e.g., during a braking operation). For instance, each of the two ends of each stator clip may be recessed back from the adjacent-most sidewall of the lug on which the stator clip is mounted.
A cargo handling system is disclosed herein. The cargo handling system includes a conveyance surface a power drive unit for moving cargo along the conveyance surface where the power drive unit disposed in the conveyance surface and a cargo detector coupled to the power drive unit. The cargo detector includes an image sensor having a sensing surface, the sensing surface being oriented towards the cargo, a shutter disposed between the image sensor and the cargo, and a pin hole disposed in the shutter.
Goodrich Lighting Systems GmbH & Co. KG (Allemagne)
Inventeur(s)
Ueberschaer, Andreas
Hessling-Von Heimendahl, Andre
Pawliczek, Carsten
Depta, Marion
Abrégé
An aircraft passenger service unit, which is configured for being installed in a passenger cabin of an aircraft, includes a seat detection sensor for determining a position and/or an orientation of at least one passenger seat, which is located in the vicinity of, in particular below, the aircraft passenger service unit.
Systems and methods for forming an oxidation protection system on a composite structure are provided. In various embodiments, the oxidation protection system comprises a boron-glass layer formed on the composite substrate and a silicon-glass layer formed over the boron-glass layer. Each of the boron-glass layer and the silicon-glass layer include a glass former and a glass modifier. The boron-glass layer includes a boron compound comprising a mixture of boron carbide (B4C) powder and cubic boron nitride (BN) powder.
C04B 35/5831 - Produits céramiques mis en forme, caractérisés par leur composition; Compositions céramiques; Traitement de poudres de composés inorganiques préalablement à la fabrication de produits céramiques à base de non oxydes à base de borures, nitrures ou siliciures à base de nitrure de bore à base de nitrure de bore cubique
C04B 35/563 - Produits céramiques mis en forme, caractérisés par leur composition; Compositions céramiques; Traitement de poudres de composés inorganiques préalablement à la fabrication de produits céramiques à base de non oxydes à base de carbures à base de carbure de bore
C04B 35/565 - Produits céramiques mis en forme, caractérisés par leur composition; Compositions céramiques; Traitement de poudres de composés inorganiques préalablement à la fabrication de produits céramiques à base de non oxydes à base de carbures à base de carbure de silicium
C04B 35/58 - Produits céramiques mis en forme, caractérisés par leur composition; Compositions céramiques; Traitement de poudres de composés inorganiques préalablement à la fabrication de produits céramiques à base de non oxydes à base de borures, nitrures ou siliciures
C04B 35/14 - Produits céramiques mis en forme, caractérisés par leur composition; Compositions céramiques; Traitement de poudres de composés inorganiques préalablement à la fabrication de produits céramiques à base d'oxydes à base de silice
A method of forming a composite component is provided. The method includes locating a fibrous preform, providing a slurry, mixing the slurry with sacrificial fibers, injecting the slurry into the fibrous preform, heating the fibrous preform, forming channels in the fibrous preform, and densifying the fibrous preform. The sacrificial fibers are suspended in the fibrous preform along an injection pathway such that heating the sacrificial fibers forms the channels along the injection pathway as the sacrificial fibers are burned away.
A silicone heater assembly is provided. The silicone heater includes a heater and a thermal pad. The thermal pad is configured to couple to the heater. The thermal pad is configured to conform to a plumbing infrastructure to be heated.
A cargo handling system is disclosed herein. The cargo handling system includes a ball panel for moving and storing cargo and a cargo restraining device disposed within the ball panel. The cargo restraining device includes a base, a cam head having a rounded base portion, the rounded base portion having a lock slot formed therein, a shaft securing the cam head to the base, and a spring-loaded lock plate configured to engage the lock slot.
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
B64C 29/00 - Aéronefs capables d'atterrir ou de décoller à la verticale, p.ex. aéronefs à décollage et atterrissage verticaux [ADAV, en anglais VTOL]
B64D 15/22 - Mise en action automatique par détecteur de givrage
88.
SOLENOID OPERATED PRESSURE CARTRIDGE FOR INFLATION SYSTEM
An inflation valve arrangement includes an actuation cavity housing connected to a pneumatic valve, the actuation cavity housing comprising an actuation cavity and a piston rod extending from the actuation cavity at least partially into a main fluid channel of the pneumatic valve in an initially extended position for securing the pneumatic valve in a closed position. The arrangement further comprises a solenoid actuated pressure cartridge connected to the actuation cavity housing. The solenoid actuated pressure cartridge comprises a self-contained source of actuation gas. In response to the solenoid actuated pressure cartridge being energized, the solenoid operated pressure cartridge is configured to release the actuation gas from the pressure cavity into the actuation cavity, thereby retracting the piston rod into the actuation cavity, and opening the pneumatic valve body to release a source of inflation gas to an inflation device.
F16K 31/42 - Moyens de fonctionnement; Dispositifs de retour à la position de repos actionnés par un fluide et au moyen d'organes actionnés électriquement dans les canalisations d'entrée ou de refoulement du moteur à fluide
F16K 24/06 - Dispositifs, p.ex. soupapes, pour la mise à l'air libre ou l'aération d'enceintes pour l'aération uniquement
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.
Disclosed is a buoyancy tube for a life raft having: a first panel including: a first panel top edge and a first panel bottom edge, the first panel top edge defines a first repeating pattern, and the first panel bottom edge defines a second repeating pattern that is a rotated version of the first panel top edge; a second panel that has a same shape as the first panel, the first and second panels connected by a first elongated seam and a second elongated seam that are non-overlapping with one another, the first and second panels, when connected, define outer an inner boundaries of the life raft, the outer boundary defines an outer polygon having outer sides and the inner boundary defines an inner polygon having inner sides such that each of the plurality of outer sides is parallel with one of the plurality of inner sides.
A joint for a composite frame includes a first composite rod, a first shell abutting the first composite rod, a second shell abutting the first composite rod and disposed opposite the first shell relative to the first composite rod. The first and second shells are joined together such that composite rod is fixed therebetween. A method of forming joints of composite frame includes forming a composite frame by interconnecting a plurality of composite rods formed by an Automated Fiber Placement (AFP) manufacturing method around a mandrel, applying a first shell to the plurality of composite rods at a first location where composite rods are interconnected, applying a second shell at the first location opposite the first shell relative to the composite rods, and joining the first and second shells together with the composite rods at the first location disposed between the first and second shells.
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.
A light system for an evacuation slide may include a readiness indicator light assembly. The readiness indicator light assembly may comprise a first light emitting diode configured to emit a first color and a second light emitting diode configured to emit a second color. The light system may be configured to power the first light emitting diode after initial deployment of the evacuation slide and to power the second light emitting diode after the internal pressure of the evacuation slide is greater than a minimum pressure threshold.
G08B 5/36 - Systèmes de signalisation optique, p.ex. systèmes d'appel de personnes, indication à distance de l'occupation de sièges utilisant une transmission électromécanique utilisant des sources de lumière visible
H05B 45/22 - Commande de la couleur de la lumière à l'aide d'un retour optique
A method of forming a B4C layer as a component of an oxidation protection system as component of oxidation protection system on a carbon-carbon composite material may include forming a liquid mixture comprising a boron-compound and a carbon-compound. The method may further include applying the liquid mixture on the carbon-carbon composite material. The boron compound may comprise boric acid (H3BO3). In various embodiments, the carbon-compound comprises phenolic resin. In various embodiments, the method further includes heating the carbon-carbon composite material after applying the liquid mixture on the carbon-carbon composite material to from a boron carbide (B4C) layer.
C23C 14/06 - Revêtement par évaporation sous vide, pulvérisation cathodique ou implantation d'ions du matériau composant le revêtement caractérisé par le matériau de revêtement
A fiber de-gassing membrane includes a plurality of membrane fibers. At least one of the membrane fibers has a first stiffness. The membrane includes reinforcing fibers. The reinforcing fibers are positioned adjacent to at least one of the membrane fibers. The reinforcing fibers have a second stiffness. The second stiffness is greater than the first stiffness.
B01D 63/04 - Modules à fibres creuses comprenant plusieurs ensembles à fibres creuses
B01D 69/02 - Membranes semi-perméables destinées aux procédés ou aux appareils de séparation, caractérisées par leur forme, leur structure ou leurs propriétés; Procédés spécialement adaptés à leur fabrication caractérisées par leurs propriétés
96.
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.
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 9/38 - Couvercles de protection ou de présentation décorative
97.
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
98.
AIRCRAFT PASSENGER CABIN LIGHT, AIRCRAFT PASSENGER CABIN LIGHTING SYSTEM, AND METHOD OF INSTALLING AN AIRCRAFT PASSENGER CABIN LIGHTING SYSTEM
Goodrich Lighting Systems GmbH & Co. KG (Allemagne)
Inventeur(s)
Hessling-Von Heimendahl, Andre
Depta, Marion
Ueberschaer, Andreas
Pawliczek, Carsten
Abrégé
An aircraft passenger cabin light. The light has: an elongated shape having a longitudinal direction (L) comprises: a cabin wall illumination assembly, which extends along the longitudinal direction (L) of the aircraft passenger cabin light and which is configured for illuminating a portion of a wall of an aircraft passenger cabin; and a plurality of personal reading light units for providing personal reading light illumination to passengers. The plurality of personal reading light units are arranged in an array extending along the longitudinal direction (L) of the aircraft passenger cabin light Said array is arranged along the cabin wall illumination assembly.
B64D 47/02 - Aménagements ou adaptations des dispositifs de signalisation ou d'éclairage
B60Q 3/44 - Agencement des dispositifs d’éclairage pour l’intérieur des véhicules; Dispositifs d’éclairage spécialement adaptés à l’intérieur des véhicules spécialement adaptés à des types spécifiques de véhicules pour les véhicules de transport en commun, p.ex. les bus Éclairage ponctuel, p.ex. lampes de lecture
F21S 8/02 - Dispositifs d'éclairage destinés à des installations fixes encastrables, p.ex. plafonniers à spots lumineux
F21W 107/30 - Utilisation ou application de dispositifs d’éclairage sur ou dans des types véhicules spécifiques pour les aéronefs
F21W 106/00 - Dispositifs d’éclairage à l’intérieur des véhicules
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.
An inflatable girt for an evacuation slide may comprise a sleeve section, an upper section coupled to the sleeve section, and a lower section coupled to at least one of the sleeve second and the upper section. The sleeve section defines a plurality of first inflatable chambers. The upper section defines a plurality of second inflatable chambers. The lower defines a plurality of third inflatable chambers.
