A method predicts an anomaly. An input image of a platform selected for inspection is identified. An output image with a number of parameters predicted for the anomaly on the platform at a future time frame is generated using the input image of the platform, the future time frame, and an anomaly analysis system in response to identifying the input image. The anomaly analysis system comprises a machine learning model system configured to output images with the number of parameters predicted for anomalies on platforms at future time frames using inputs comprising input images of the platforms and the future time frames. A number of actions is performed based on the output image.
G06V 10/77 - Traitement des caractéristiques d’images ou de vidéos dans les espaces de caractéristiquesDispositions pour la reconnaissance ou la compréhension d’images ou de vidéos utilisant la reconnaissance de formes ou l’apprentissage automatique utilisant l’intégration et la réduction de données, p. ex. analyse en composantes principales [PCA] ou analyse en composantes indépendantes [ ICA] ou cartes auto-organisatrices [SOM]Séparation aveugle de source
G06V 10/82 - Dispositions pour la reconnaissance ou la compréhension d’images ou de vidéos utilisant la reconnaissance de formes ou l’apprentissage automatique utilisant les réseaux neuronaux
A method for manufacturing a workpiece. A job is created as part of a workflow to manufacture the workpiece using a numeric control machine. The job identifies tasks in the workflow to manufacture the workpiece. A standardized computer-aided design model is created in a standardized format from a computer-aided design model and stored in a digital thread. Simulations are performed using information in the digital thread used as inputs to obtain simulation results. The information is in a simulator format used by each of the simulators. The simulation results are stored in the standardized format in the digital thread. A numeric control program in a numeric control machine format utilized by the numeric control machine is created using product manufacturing information and geometry for the workpiece in the standardized computer-aided design model in the digital thread. The workpiece is manufactured using the numeric control program and the numeric control machine.
G05B 19/4097 - 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'un programme sous forme numérique caractérisée par l'utilisation de données de conception pour commander des machines à commande numérique [CN], p. ex. conception et fabrication assistées par ordinateur CFAO
3.
LANDING GEAR ASSEMBLIES, ROTORCRAFT AND ROTORCRAFT METHODS
A landing gear assembly for rotorcraft includes a shock absorber, a ground support assembly and an airframe linkage assembly. The shock absorber includes a force sensor to detect a pressure of an incompressible fluid within the shock absorber and a temperature sensor to detect a temperature of the fluid. The ground support assembly is linked to the shock absorber and includes an axle and a ground contact element movable in relation to the axle. The linkage assembly is linked to the shock absorber and/or the ground support assembly and includes a position sensor to detect movement of the axle between compressed and uncompressed conditions of the shock absorber. Various rotorcraft include one, two, three or more landing gear assemblies and an attitude control system. Various rotorcraft methods process sensor signals from one, two, three or more landing gear assemblies at the attitude control system to provide various rotorcraft functions.
Method and apparatus to measure hole normality are disclosed. An example apparatus for measuring a normality of an aperture relative to a surface includes a shaft to be inserted into the aperture of the surface, a body carrying the shaft, a carriage pivotable relative to the body, the carriage supporting a probe to contact the surface, and displacement indicator supported by the body, the displacement indicator to be moved by the carriage to measure a displacement of the probe as the body and the carriage are rotated about the shaft.
G01B 5/245 - Dispositions pour la mesure caractérisées par l'utilisation de techniques mécaniques pour mesurer des angles ou des cônesDispositions pour la mesure caractérisées par l'utilisation de techniques mécaniques pour tester l'alignement des axes pour tester la perpendicularité
G01B 3/46 - Calibres à tampon pour les dimensions intérieures avec des surfaces de contact dont l'écartement est fixe, mais peut être réglé à l'avance
G01B 5/14 - Dispositions pour la mesure caractérisées par l'utilisation de techniques mécaniques pour mesurer une distance ou une marge entre des objets ou des ouvertures espacés
Example implementations are directed to a method and system for collision avoidance for an aircraft traversing a flight path. The method and system described herein provides an architecture to address the full gamut of complexity that arises when dealing with possible conflicts during aircraft flight. The collision avoidance method and system disclosed herein first receives multiple streams of potential conflict information that not only considers direct obstacles on the flight path of the aircraft, but also considers contextual obstacles that are within a perimeter of the flight path. Once the possible objects are considered, a plurality of alternate flight paths are calculated and the alternate flight path with an acceptable miss distance with a possible obstacle (and minimized deviation from the original flight path) is selected and the aircraft traversing the flight path deviates from the original flight path to the alternate flight path to avoid the collision(s).
A compact bevel gear split torque gearbox is disclosed. A disclosed example apparatus includes a first pinion to receive an input torque, a second pinion operatively coupled to the first pinion, an output gear operatively coupled to the first and second pinions, and a continuously variable (CV) adapter operatively coupled between the first and second pinions, the CV adapter having a helical spline.
F16H 1/20 - Transmissions à engrenages pour transmettre un mouvement rotatif sans engrenages à mouvement orbital comportant plus de deux organes engrenés
F16D 3/06 - Accouplements extensibles, c.-à-d. avec moyens permettant le mouvement entre parties accouplées durant leur entraînement adaptés à des fonctions particulières spécialement adaptés pour permettre un déplacement axial
F16H 57/038 - Boîtes de vitesses pour engrenages coniques
7.
ALERTING SYSTEM FOR HIGHLY AUTOMATED m:N AERIAL VEHICLE OPERATIONS
Techniques for operating a plurality of autonomous aerial vehicles are presented. The techniques may include: receiving, by a computer, a plurality of trigger event indications, where the trigger event indications represent a plurality of trigger events concerning the autonomous aerial vehicles, where a respective trigger event indication is associated with a respective task; retrieving, from an electronic database, for each trigger event indication, respective priority data, from which priority data for the trigger event indications is obtained, where respective priority data for a respective trigger event indication includes respective task time data and respective severity data; ranking, by the computer, and in real time, a plurality of tasks associated with the trigger event indications, from which a ranked task list is obtained, where the ranking is based on at least the priority data for the trigger event indications; and providing the ranked task list.
In one example, a method for drilling holes in a substrate is presented. The method comprises focusing a laser relative to a surface of the substrate at a first drilling location in the substrate. The laser is applied to the surface of the substrate for a first drilling round, the first drilling round comprising one or more drilling passes wherein the laser is moved in x and y dimensions in a predetermined pattern. A focal plane of the laser is adjusted relative to the surface of the substrate in the z dimension. The laser is applied to the surface of the substrate at the first drilling location for a second drilling round, the second drilling round comprising one or more drilling passes wherein the laser is moved in x and y dimensions in the predetermined pattern.
B23K 26/382 - Enlèvement de matière par perçage ou découpage par perçage
B23K 26/402 - Enlèvement de matière en tenant compte des propriétés du matériau à enlever en faisant intervenir des matériaux non métalliques, p. ex. des isolants
A tracking unit configured to connect to a robotic device and move across a surface of an object. The tracking unit includes a body, one or more distance sensors mounted to a first side of the body and configured to detect a distance from the object, and one or more peripheral sensors mounted to a second side of the body and configured to detect a peripheral feature. A controller is configured to receive signals from the one or more distance sensors and the one or more peripheral sensors. The controller is configured to position the body a fixed distance away from the object and to prevent contact between the body and the peripheral feature.
A method includes obtaining pressure data and temperature data for gas in shock struts of a plurality of landing gear of an aircraft. The method includes obtaining load data for each landing gear from one or more load sensors associated with the landing gear. The method includes determining a gross weight, a center of gravity, or both, of the aircraft based on a pitch of the aircraft, the pressure data, the temperature data, the load data, model parameters, or combinations thereof. The method includes accumulating pressure data, temperature data, load data, and the pitch of the aircraft as calibration data for transitions of shock struts from dynamic states to static states. The method includes obtaining updated model parameters based on the calibration data. The method also includes replacing one or more of the model parameters with corresponding updated model parameters in response to satisfaction of a threshold.
G01G 19/07 - Appareils ou méthodes de pesée adaptés à des fins particulières non prévues dans les groupes pour peser des objets à roues ou roulants, p. ex. des véhicules pour peser des avions
A device including an outer shell having a first longitudinal axis and a first arcuate shape. The outer shell is opaque to ultraviolet light and to visible light. The device also includes an inner shell having a second longitudinal axis. The inner shell is connected longitudinally to the outer shell along a first longitudinal length and a second longitudinal length. The inner shell has a second arcuate shape different than the first arcuate shape. A chamber is disposed between the outer shell and the inner shell. The chamber is defined by a difference between the first arcuate shape and the second arcuate shape. The device also includes an ultraviolet light source disposed along the second longitudinal axis.
A61L 2/10 - Procédés ou appareils de désinfection ou de stérilisation de matériaux ou d'objets autres que les denrées alimentaires ou les lentilles de contactAccessoires à cet effet utilisant des phénomènes physiques des radiations des ultraviolets
A computer-implemented method for assessing sustainability impacts of an alternative option. The method includes accessing a sustainability assessment tool which includes pre-defined templates to guide users through structured sustainability questions. The method includes receiving input data for an alternative option related to a plurality of sustainability categories and integrating the input data into a framework comprising a plurality of sustainability sub-categories. The method includes analyzing the input data and identifying relative risks and benefits associated with the alternative option in comparison with a baseline option. The method includes generating comparative visual outputs to visually represent the relative sustainability risks and benefits of the alternative option.
A coupling system is configured to removably connect to a cart. The coupling system includes a connecting arm, and an adapter coupled to the connecting arm. The adapter is configured to removably secure the connecting arm to one or more stanchions of the cart. One or more securing clamps can be coupled to the connecting arm. The one or more securing clamps are configured to removably secure the coupling system in a stowed position to a beam of the cart.
A toggle clamp tool system includes a pair of toggle clamps and a tool. Each toggle clamp includes a clamp base and a clamp arm. The clamp base is configured to be pivotably coupled to a mounting point on a structure. The clamp arm is pivotably coupled at one end to the clamp base at an arm-base pivot point, and has a clamp foot on an opposite end for bearing against a surface of the structure. The clamp arm is movable from a disengaged position into an over-center position from which the clamp arm is unable to pivot away from the surface and back toward the disengaged position. The tool is configured to be removably mounted on the clamp base of each of the toggle clamps when coupled to the structure.
F16B 2/18 - Brides ou colliers, c.-à-d. dispositifs de fixation dont le serrage est effectué par des forces effectives autres que la résistance à la déformation inhérente au matériau dont est fait le dispositif utilisant des cames, des leviers, des excentriques ou des rotules
B64F 5/10 - Fabrication ou assemblage d’aéronefs, p. ex. gabarits à cet effet
17.
High Efficiency Directional Stabilization of Lasers
A laser directional stabilization system corrects pointing errors in a laser used to transmit data in free space optical links. The system includes a nutator that nutates a laser beam over the face of an optical fiber at a receiver. Light entering the fiber is used as a sensor to achieve for stabilization. The laser beam is nutated at a single, relatively high frequency using resonant amplifiers driving linear actuators. Knowledge of the nutation command and the time varying intensity of light received at the center of the fiber permits generation an error that is used in a feedback loop to reduce laser pointing error.
G02B 26/08 - Dispositifs ou dispositions optiques pour la commande de la lumière utilisant des éléments optiques mobiles ou déformables pour commander la direction de la lumière
F16M 11/12 - Moyens pour la fixation des appareilsMoyens permettant le réglage des appareils par rapport au banc permettant la rotation dans plus d'une direction
G01J 1/42 - Photométrie, p. ex. posemètres photographiques en utilisant des détecteurs électriques de radiations
H04B 10/079 - Dispositions pour la surveillance ou le test de systèmes de transmissionDispositions pour la mesure des défauts de systèmes de transmission utilisant un signal en service utilisant des mesures du signal de données
H04B 10/118 - Dispositions spécifiques à la transmission en espace libre, c.-à-d. dans l’air ou le vide spécialement adaptées aux communications par satellite
18.
CONSTRAINT BASED INFERENCE AND MACHINE LEARNING SYSTEM
A method including receiving a pre-determined constraint on user actions. A constraint vector is generated based on the pre-determined constraint. The constraint vector is input into a machine learning model. A first output is generated from the machine learning model by executing the machine learning model using the constraint vector as a first input to the machine learning model. The constraint vector is converted into a legal action mask. A probability vector is generated by executing a masked softmax operator. The masked softmax operator takes, as a second input, the first output. The masked softmax operator takes, as a third input, the legal action mask. The masked softmax operator generates, as a second output, the probabilities vector. Action outputs are generated by applying a sampling system to the probability vector. The action outputs include a subset of the user actions, and wherein the subset includes only allowed user actions.
G06N 3/047 - Réseaux probabilistes ou stochastiques
G05B 13/02 - Systèmes de commande adaptatifs, c.-à-d. systèmes se réglant eux-mêmes automatiquement pour obtenir un rendement optimal suivant un critère prédéterminé électriques
A cryogenic fuel tank system for an aircraft and method for forming. The cryogenic fuel tank system includes a first outer sheet, an inner sheet, a second outer sheet, and a space between the first outer sheet and the second outer sheet. The inner sheet is bonded to the first outer sheet at a first set of bond locations. The inner sheet is bonded to the second outer sheet at a second set of bond locations. The first set of bond locations are offset from the second set of bond locations. The space comprises a vacuum. The inner sheet extends between the first outer sheet and the second outer sheet and forms an integrally formed support structure between the first outer sheet and the second outer sheet.
A holding system is configured to hold a bucket. The bucket is configured to receive adhesive fluid from an adhesive meter mix machine. The holding system includes a base including a main body, and a stem extending from the main. The stem includes an extension beam and a bent arm that is angled in relation to the extension beam. A holder is rotationally coupled to the bent arm. The holder is configured to retain the bucket.
F16M 11/22 - Infrastructure avec ou sans roues à hauteur sensiblement constante, p. ex. avec colonne ou pieds de longueur constante
F16M 11/08 - Moyens pour la fixation des appareilsMoyens permettant le réglage des appareils par rapport au banc permettant la rotation autour d'un axe vertical
B67D 7/02 - Appareils ou dispositifs pour transférer des liquides à partir de récipients ou de réservoirs de stockage en vrac vers des véhicules ou des récipients portables, p. ex. pour la vente au détail pour transférer des liquides autres que des carburants ou des lubrifiants
21.
FORMING A COMPOSITE STRUCTURE USING PRE-KITTED PLY SETS
A composite structure and methods of forming a composite structure are presented. The composite structure comprises a plurality of pre-kitted ply sets with a same ply layup positioned to form continuous plies. Each pre-kitted ply set of the plurality of pre-kitted ply sets comprises a first ply having a first shape and an overhang on a first side of the ply layup; and a second ply overlying the first ply, the second ply having a second shape.
B29C 70/30 - Façonnage par empilage, c.-à-d. application de fibres, de bandes ou de feuilles larges sur un moule, un gabarit ou un noyauFaçonnage par pistolage, c.-à-d. pulvérisation de fibres sur un moule, un gabarit ou un noyau
B29C 70/54 - Parties constitutives, détails ou accessoiresOpérations auxiliaires
B29L 31/30 - Véhicules, p. ex. bateaux ou avions, ou éléments de leur carrosserie
A beacon detection system includes a camera, a motion detection device associated with the camera, and one or more processors. The one or more processors process, using a motion compensation technique, a video feed captured by the camera and determine light flickering frequency information associated with a plurality of regions of the video feed. The one or more processors determine, using a filtering technique associated with a beacon frequency, and based on the light flickering frequency information, a set of one or more regions, of the plurality of regions of the video feed, that are associated with the beacon frequency. The one or more processors provide a filtered video feed that includes video content of the video feed that is only associated with the set of one or more regions of the video feed.
H04N 23/68 - Commande des caméras ou des modules de caméras pour une prise de vue stable de la scène, p. ex. en compensant les vibrations du boîtier de l'appareil photo
H04N 23/71 - Circuits d'évaluation de la variation de luminosité
H04N 23/745 - Détection de la fréquence de scintillement ou suppression du scintillement, le scintillement étant causé par l'éclairage, p. ex. par l'éclairage d'un tube fluorescent ou d'une LED pulsée
23.
REFERENCE STANDARD FOR EVALUATION OF A NON-DESTRUCTIVE INSPECTION DEVICE AND ASSOCIATED SYSTEM AND METHOD
Disclosed herein is a reference standard for evaluation of a non-destructive inspection (NDI) device and associated system and method. The reference standard includes an elongated tool with an outer surface having an outer inspection surface defining a constant radius and an outer testing surface contiguous with the outer inspection surface. The reference standard incorporates various features designed to evaluate different performance parameters of the NDI system into a single device. The features may include a plurality of alignment mark, first inset parallel surfaces, a pair of parallel inspection lines, an angled distortion line, a plurality of radial index marks, and a plurality of lateral index marks.
G01N 29/22 - Recherche ou analyse des matériaux par l'emploi d'ondes ultrasonores, sonores ou infrasonoresVisualisation de l'intérieur d'objets par transmission d'ondes ultrasonores ou sonores à travers l'objet Détails
Systems and methods of aircraft modal suppression informed by an underlying non-uniform vertical turbulence model and uniform lateral turbulence model. The systems and methods include receiving a plurality of signals from on-board inertial sensors of an aircraft, utilizing the plurality of signals to generate a plurality of observers, utilizing the observers to determine a control law command for controlling one or more control surfaces of the aircraft, and moving the one or more control surfaces of the aircraft in accordance with the determined control law command such that lateral mode vibrations of the aircraft are diminished.
B64C 13/16 - Dispositifs amorçant la mise en œuvre actionnés automatiquement, p. ex. répondant aux détecteurs de rafales
F16F 15/00 - Suppression des vibrations dans les systèmesMoyens ou dispositions pour éviter ou réduire les forces de déséquilibre, p. ex. dues au mouvement
Examples are disclosed that relate to an electric machine that achieves independent speed, variable frequency power generation and has increased power density, efficiency, reliability, and reduced complexity relative to conventional electric machines. In one example, an electric machine includes a stator, a first stationary winding coupled to the stator, a second stationary winding coupled to the stator, and a rotor. The second stationary winding includes a plurality of winding segments corresponding to a number of phases of power of the electric machine. The rotor extends through the stator and the second stationary winding. The rotor includes a plurality of rotor segments. Each rotor segment of the plurality of rotor segments includes a plurality of pole lobes that extend radially from the rotor segment. Two or more pole lobes of each rotor segment are located on opposing sides of a corresponding winding segment of the second stationary winding.
A composite structure is presented. The composite structure comprises a plurality of cured composite plies with a void creating a separation within the plurality of cured composite plies. The composite structure comprises a number of injection holes connecting the void to an exterior of the plurality of cured composite plies. The composite structure comprises a cured resin with a plurality of electromagnetically steerable fibers within the separation forming the composite repair and configured to transmit forces to composite plies in contact with the composite repair, wherein mechanical properties of the composite repair are improved in the direction of a set of the plurality of electromagnetically steerable fibers with less knock-down.
B29C 73/02 - Réparation d'articles faits de matières plastiques ou de substances à l'état plastique, p. ex. d'objets façonnés ou fabriqués par utilisation de techniques couvertes par la présente sous-classe ou la sous-classe utilisant un liquide ou un matériau pâteux
B29C 70/88 - Façonnage de matières composites, c.-à-d. de matières plastiques comprenant des renforcements, des matières de remplissage ou des parties préformées, p. ex. des inserts caractérisées principalement par des propriétés spécifiques, p. ex. électriquement conductrices ou renforcées localement
A substrate for solar cells is fabricated such that an area of the substrate remains exposed when at least one solar cell having at least one cropped corner that defines a corner region is attached to the substrate; the area of the substrate that remains exposed includes one or more conductors printed on the substrate; and electrical connections between the solar cell and the conductors are made in the corner region resulting from the cropped corner of the solar cell. The substrate may also include buried conductors for making series connections that determine a flow of power through a plurality of solar cells, including corner-to-corner and column-to-column connections for the plurality of solar cells that are attached to the substrate in a two-dimensional (2-D) grid of an array. The substrate may also be covered by a polyimide overlay for preventing electrostatic discharge (ESD).
H10F 19/00 - Dispositifs intégrés, ou ensembles de plusieurs dispositifs, comprenant au moins une cellule photovoltaïque couverte par le groupe , p. ex. modules photovoltaïques
H02S 40/34 - Composants électriques comprenant une connexion électrique structurellement associée au module PV, p. ex. boîtes de jonction
H10F 10/142 - Cellules photovoltaïques ayant uniquement des barrières de potentiel du type à homojonction PN comportant plusieurs homojonctions PN, p. ex. cellules dites "tandem"
H10F 19/50 - Dispositifs intégrés comportant au moins une cellule photovoltaïque et d’autres types de composants semi-conducteurs ou à l’état solide
H10F 19/70 - Dispositifs intégrés, ou ensembles de plusieurs dispositifs, comprenant au moins une cellule photovoltaïque couverte par le groupe , p. ex. modules photovoltaïques comportant des diodes de dérivation
H10F 19/75 - Dispositifs intégrés, ou ensembles de plusieurs dispositifs, comprenant au moins une cellule photovoltaïque couverte par le groupe , p. ex. modules photovoltaïques comportant des diodes de dérivation les diodes de dérivation étant intégrées ou directement associées aux cellules photovoltaïques, p. ex. formées dans ou sur le même substrat
H10F 19/80 - Encapsulations ou conteneurs pour des dispositifs intégrés, ou des ensembles de plusieurs dispositifs, comportant des cellules photovoltaïques
H10F 19/90 - Structures pour la connexion des cellules photovoltaïques, p. ex. interconnexions ou espaceurs isolants
H10F 77/00 - Détails de structure des dispositifs couverts par la présente sous-classe
H10F 77/14 - Forme des corps semi-conducteursFormes, dimensions relatives ou dispositions des régions semi-conductrices au sein des corps semi-conducteurs
H10F 77/169 - Films minces semi-conducteurs sur des substrats métalliques ou isolants
In some implementations, a system within a flight deck of an aircraft determines, based on line-of-sight data associated with an aircraft operator stationed within the flight deck of the aircraft, a field of view (FOV) of the aircraft operator. The system determines display configuration information based on a set of one or more visual references derived from the FOV of the aircraft operator. The system updates a projection display component that is positioned within the flight deck and within the FOV of the aircraft operator to display at least visual representation information associated with the set of one or more visual references based on the display configuration information.
B64D 45/00 - Indicateurs ou dispositifs de protection d'aéronefs, non prévus ailleurs
G06F 3/01 - Dispositions d'entrée ou dispositions d'entrée et de sortie combinées pour l'interaction entre l'utilisateur et le calculateur
G06F 3/14 - Sortie numérique vers un dispositif de visualisation
G06T 7/70 - Détermination de la position ou de l'orientation des objets ou des caméras
G09G 3/00 - Dispositions ou circuits de commande présentant un intérêt uniquement pour l'affichage utilisant des moyens de visualisation autres que les tubes à rayons cathodiques
29.
Fast Acquisition Laser Communications using a Minimum Average Distance Shift Process
A method converges a laser beam. A sequence of shifts is identified from a simulation of sequences of shifts that move an average distance of test points from a center of a test quad cell sensor to reach a convergence on the test quad cell sensor, wherein the sequence of shifts moves the average distance of the test points to converge on the center with at least one of a lowest number of shifts or a lowest average number of shifts. A position of a mirror receiving the laser beam is changed using the sequence of shifts to shift the laser beam towards the convergence on a quad cell sensor.
A system for processing a workpiece includes a constraining container, a pressure-triggered coupling, and an expandable medium. The constraining container includes an interior volume and is configured to enclose at least a portion of the workpiece to be processed. The pressure-triggered coupling is configured to secure the constraining container in a closed configuration and is configured to release the constraining container upon an interior pressure of the interior volume of the constraining container reaching a trigger pressure. The expandable medium is configured to be disposed within the interior volume between at least a portion of the constraining container and at least a portion of the workpiece and is configured to expand such that the expandable medium applies a positive pressure to the constraining container and the workpiece.
A system for fabricating a workpiece includes a case that includes an interior volume. The case is configured to enclose at least a portion of the workpiece to be fabricated. The system includes an expandable medium disposed within the interior volume between the case and at least the portion of the workpiece. The expandable medium is configured to expand within the case such that the expandable medium applies positive pressure to at least the portion of the workpiece enclosed by the case.
B29C 70/44 - Façonnage ou imprégnation par compression pour la fabrication d'objets de longueur définie, c.-à-d. d'objets distincts utilisant une pression isostatique, p. ex. moulage par différence de pression, avec un sac à vide, dans un autoclave ou avec un caoutchouc expansible
B29C 70/54 - Parties constitutives, détails ou accessoiresOpérations auxiliaires
32.
SYSTEM AND METHOD FOR ADJUSTING ENGINE POWERSETTING FOR MINIMUM EQUIPMENT LIST DISPATCH
An aircraft includes one or more processors configured to receive input identifying a first equipment item as inoperative. The one or more processors are configured to select, based on the input identifying the first equipment item as inoperative, an adjustment factor to be applied during engine performance calculations for a particular planned flight of the aircraft. The one or more processors are configured to determine, based on the adjustment factor and ambient condition data associated with the aircraft, a set of engine performance planning metrics for the particular planned flight. The one or more processors are configured to determine, based on the set of engine performance planning metrics, a weight penalty, a fuel penalty, or both, for the particular planned flight.
Methods of performing gap resin infusion are presented. A resin is injected into a resin infusion chamber of a resin infusion mold comprising a first portion and a second portion while maintaining a temperature differential between the first portion and the second portion. An infused preform is formed by forcing the resin into a dry fiber preform located in the resin infusion chamber while maintaining the temperature differential between the first portion and the second portion of the resin infusion mold.
B29C 70/48 - Façonnage ou imprégnation par compression pour la fabrication d'objets de longueur définie, c.-à-d. d'objets distincts utilisant des moules opposables, p. ex. pour déformer des préimprégnés [SMC] ou des "prepregs" avec une imprégnation des renforcements dans le moule fermé, p. ex. moulage par transfert de résine [RTM]
B29C 35/04 - Chauffage ou durcissement, p. ex. réticulation ou vulcanisation avec des liquides, des gaz ou de la vapeur d'eau
B29C 70/54 - Parties constitutives, détails ou accessoiresOpérations auxiliaires
B29L 31/30 - Véhicules, p. ex. bateaux ou avions, ou éléments de leur carrosserie
34.
LOCKING A BANK ANGLE PARAMETER AND A GROUND SPEED PARAMETER
A flight management system (FMS) of an aircraft may determine that a leg of a lateral trajectory profile, of a flight plan for the aircraft, is active. The FMS may determine, based on determining that the leg of the lateral trajectory profile is active, that a lateral distance between the aircraft and an end waypoint associated with the leg satisfies a lateral distance threshold and may therefore perform an update to the lateral trajectory profile to lock a bank angle parameter to a particular bank angle value. The FMS may determine that a transition, which is associated with the end waypoint and another leg of the lateral trajectory profile, is active and may therefore perform an update to the lateral trajectory profile to lock a ground speed parameter to a particular ground speed value.
A friction damper includes a central axis, a damper housing, a bearing assembly, and a loading assembly. The damper housing includes a bore extending along the central axis. The bearing assembly is situated in the bore and is configured to rotate in a load direction about the central axis relative to the damper housing in response to a torsional load applied to the bearing assembly. The loading assembly is situated in the bore and is configured to apply an axial load to the bearing assembly along the central axis.
F16F 7/04 - Amortisseurs de vibrationsAmortisseurs de chocs avec surfaces de friction à rotation relative qui sont pressées l'une contre l'autre dans la direction de l'axe de rotation
36.
Fast Acquisition Laser Communications using a Variable Binary Shift Process
A method converges a laser beam. A sequence of shifts having a first shift is identified from first shifts in a simulation of sequences of shifts performed for test points to reach a convergence on a test quad cell sensor in which sequence of shifts having the first shift has at least one of a lowest number of shifts or a lowest average number of shifts to reach the convergence for the test points in the simulation, wherein each shift after the first shift is one half of a prior shift. A position of a mirror receiving the laser beam is changed using the first shift in the sequence of shifts. The position of the mirror is changed such that each shift after the first shift in the sequence of shifts is one half of the prior shift to shift the laser beam towards convergence on a quad cell sensor.
G02B 26/08 - Dispositifs ou dispositions optiques pour la commande de la lumière utilisant des éléments optiques mobiles ou déformables pour commander la direction de la lumière
H04B 10/11 - Dispositions spécifiques à la transmission en espace libre, c.-à-d. dans l’air ou le vide
37.
Fast Acquisition Laser Communications using a Split Variable Shift Process
A method converges a laser beam A sequence of shifts is identified from a simulation of shifts for test points to reach a convergence on a test quad cell sensor in which the sequence of shifts has at least one of a lowest number of shifts or a lowest average number of shifts to reach the convergence for the test points in the simulation. A shift after a prior shift in the sequence of shifts is based on a starting quad from which the prior shift occurs and a subsequent quad in which a detection occurs in a quad cell sensor in response to the prior shift. A position of a mirror receiving the laser beam is changed using the sequence of shifts to shift the laser beam towards the convergence on the quad cell sensor.
A method converges a laser beam. A sequence of shifts is identified from a simulation of sequences of shifts that move an average distance of test points from a center of a test quad cell sensor to reach a convergence on the test quad cell sensor, wherein a shift in the sequence of shifts after a prior shift in the sequence of shifts is based on a starting quad from which the prior shift occurs and a subsequent quad in which a detection occurs in a quad cell sensor in response to the prior shift. A position of a mirror receiving the laser beam is changed using the sequence of shifts to converge on the center of the quad cell sensor.
H04B 10/118 - Dispositions spécifiques à la transmission en espace libre, c.-à-d. dans l’air ou le vide spécialement adaptées aux communications par satellite
Composite structures and methods of forming composite structures are presented. A composite structure comprises a first plurality of prepreg plies, a second plurality of prepreg plies, and an infused functional structure between the first plurality of prepreg plies and the second plurality of prepreg plies. The infused functional structure comprises a first number of insulative layers, a second number of insulative layers, a functional ply comprising a number of functional components between the first number of insulative layers and the second number of insulative layers, and a resin infused into the first number of insulative layers and the second number of insulative layers.
B32B 27/12 - Produits stratifiés composés essentiellement de résine synthétique adjacente à une couche fibreuse ou filamenteuse
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
B29K 105/24 - Présentation, forme ou état de la matière moulée réticulée ou vulcanisée
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 7/12 - Liaison entre couches utilisant des adhésifs interposés ou des matériaux interposés ayant des propriétés adhésives
B32B 27/18 - Produits stratifiés composés essentiellement de résine synthétique caractérisée par l'emploi d'additifs particuliers
B32B 37/12 - Procédés ou dispositifs pour la stratification, p. ex. par polymérisation ou par liaison à l'aide d'ultrasons caractérisés par l'usage d'adhésifs
B32B 38/00 - Opérations auxiliaires liées aux procédés de stratification
40.
SYSTEM AND METHOD FOR IDENTIFYING OBSTACLES IN RELATION TO AN AIRCRAFT
An aircraft is configured to travel between a departure airport and an arrival airport. A control unit is in communication with a user interface. The control unit is configured to: (a) receive a first dataset and a second dataset, wherein the first dataset includes first data in a first format, wherein the second dataset includes second data in a second format, and wherein each of the first dataset and the second dataset includes information regarding obstacles, (b) compare the first dataset with the second dataset to determine a quality check of the information within the first dataset and the second dataset, and (c) output one or more signals to the user interface regarding the obstacles and the quality check. The aircraft is configured to be operated in relation to the obstacles.
A method of predicting the probability of fracture toughness failure of a metallic part. The method includes receiving static mechanical property data for a metallic part. The method further includes determining a predicted probability of fracture toughness failure for the metallic part using a selected statistical model. The method further includes flagging, to perform fracture toughness testing, the metallic part based on the predicted probability of fracture toughness failure being over a threshold.
G06F 30/27 - Optimisation, vérification ou simulation de l’objet conçu utilisant l’apprentissage automatique, p. ex. l’intelligence artificielle, les réseaux neuronaux, les machines à support de vecteur [MSV] ou l’apprentissage d’un modèle
42.
Systems and Methods to Jettison Fuel from an Aircraft
A system to jettison fuel from an aircraft. The system includes one or more fuel tanks configured to contain the fuel in a pressurized state. Fuel lines extend from the one or more fuel tanks with the fuel lines configured to move the fuel while in a gaseous state. A nozzle is connected to one of the fuel lines with the nozzle having a passage that moves the fuel along a length of the nozzle and out through a distal end of the nozzle.
Shims having guided fracture lines are disclosed. An example apparatus includes a shim to be positioned between a first component and a second component, the first component to be fastened to the second component, and a guided fracture line positioned in the shim, the guided fracture line defining a joint portion of the shim and a removable portion of the shim, the removable portion of the shim to extend outside of a peripheral edge of one of the first component or the second component, the guided fracture line to enable removal of the removable portion after the first component is fastened to the second component.
Techniques for assessing an operational condition of an uncrewed air transport platform are presented. The techniques include: arranging the uncrewed aircraft and at least one external sensor in proximity to each other, where the external sensor(s) include a vibration sensor; directing the external sensor(s) to the uncrewed aircraft to sense at an indicated location on the uncrewed aircraft; executing one or more operations of the uncrewed aircraft; acquiring sensor data of the uncrewed aircraft from the at least one external sensor; and analyzing the sensor data, from which one or more degradation conditions in the uncrewed aircraft are diagnosed.
Methods and apparatus for multi-layered integrity validation of vision-based vehicle guidance are disclosed. A disclosed example system includes an image sensor carried by a vehicle, the image sensor to identify light sources of a ground-based pattern display, wherein a spatial arrangement of varying distances between the light sources defines a light pattern array, and at least one processor circuitry to perform a multi-layer integrity validation corresponding to the light pattern array based on the identified light sources for guidance of the vehicle via the light pattern array.
G06V 20/58 - Reconnaissance d’objets en mouvement ou d’obstacles, p. ex. véhicules ou piétonsReconnaissance des objets de la circulation, p. ex. signalisation routière, feux de signalisation ou routes
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
G06T 5/20 - Amélioration ou restauration d'image utilisant des opérateurs locaux
G06T 7/70 - Détermination de la position ou de l'orientation des objets ou des caméras
G06V 10/762 - Dispositions pour la reconnaissance ou la compréhension d’images ou de vidéos utilisant la reconnaissance de formes ou l’apprentissage automatique utilisant le regroupement, p. ex. de visages similaires sur les réseaux sociaux
G06V 20/17 - Scènes terrestres transmises par des avions ou des drones
48.
METHOD AND SYSTEM FOR REDUCING A TEMPERATURE DIFFERENTIAL ACROSS A FLIGHT VEHICLE
Method and system for reducing a temperature differential across a flight vehicle. The system includes an exterior of the flight vehicle. The exterior of the flight vehicle includes a first exterior panel being at a first initial temperature and a second exterior panel being at a second initial temperature to define an initial temperature differential. A fluid loop, containing a working fluid, is coupled to the first exterior panel and the second exterior panel such that heat is transferred from the first exterior panel to the working fluid to decrease the first initial temperature of the first exterior panel to a first altered temperature, and to heat the working fluid. The heated working fluid is circulated from the first exterior panel and used to heat the second exterior panel to a second altered temperature greater than the second initial temperature.
A forming end effector and methods of use are presented. Methods of forming a composite material onto a mandrel are presented. A forming end effector carrying the composite material is positioned over the mandrel. The forming end effector is connected to the mandrel. The composite material is swept onto the mandrel using sweepers of the forming end effector.
B29C 70/34 - Façonnage par empilage, c.-à-d. application de fibres, de bandes ou de feuilles larges sur un moule, un gabarit ou un noyauFaçonnage par pistolage, c.-à-d. pulvérisation de fibres sur un moule, un gabarit ou un noyau et façonnage ou imprégnation par compression
B29C 70/44 - Façonnage ou imprégnation par compression pour la fabrication d'objets de longueur définie, c.-à-d. d'objets distincts utilisant une pression isostatique, p. ex. moulage par différence de pression, avec un sac à vide, dans un autoclave ou avec un caoutchouc expansible
B29L 31/30 - Véhicules, p. ex. bateaux ou avions, ou éléments de leur carrosserie
50.
SYSTEMS AND METHODS FOR HARVESTING ENERGY FROM A FLUSH CYCLE OF A TOILET
A system and a method include a toilet, and an energy harvester coupled to the toilet. The energy harvester is configured to convert vacuum force, which flushes contents from the toilet, into electrical energy. The energy harvester is further configured to provide the electrical energy to one or more components.
F03D 9/25 - Mécanismes moteurs à vent caractérisés par l’appareil entrainé l’appareil étant un générateur électrique
F03D 9/32 - Mécanismes moteurs à vent spécialement adaptés à l’installation dans des endroits particuliers sur des objets mobiles, p. ex. des véhicules
F03D 9/34 - Mécanismes moteurs à vent spécialement adaptés à l’installation dans des endroits particuliers sur des objets stationnaires ou des structures stationnaires faites par l’homme
51.
TENSION LOAD FIXTURE AND METHOD FOR EVALUATING FRACTURE BEHAVIOR OF A COMPOSITE MATERIAL
A specimen for mechanical loading analysis includes a body having a first region, a second region, and a third region. The third region defines a first chamfered edge and a second chamfered edge. The specimen further includes a notch defined by the body and separating the first region from the second region. The notch is at least partially defined by a first tapered edge of the first region and a second tapered edge of the second region. The notch includes a notch tip located at an intersection of the first region, the second region, and the third region of the body.
G01N 3/08 - Recherche des propriétés mécaniques des matériaux solides par application d'une contrainte mécanique par application d'efforts permanents de traction ou de compression
52.
Pick and Place End Effector Configured to Form a Kink
A pick and place end effector configured to form a kink in a composite laminate. The pick and place end effector comprises a vacuum lift face configured to hold the composite laminate and move from a flat configuration to a forming configuration with an angle in the vacuum lift face to form the kink in the composite laminate; a number of motors configured to move the vacuum lift face between the flat configuration and the forming configuration; and a number of restraints configured to clamp portions of a composite laminate on opposite sides of the kink on the vacuum lift face during movement between the flat configuration and the forming configuration.
A tailorable composite material longitudinal radius filler made from harvested, recycled dry fiber material and a composite material assembly a longitudinal radius filler cavity filled with the tailorable composite material longitudinal radius filler and methods of manufacture are presently disclosed herein.
B29C 70/54 - Parties constitutives, détails ou accessoiresOpérations auxiliaires
B29K 63/00 - Utilisation de résines époxy comme matière de moulage
B29K 105/12 - Présentation, forme ou état de la matière moulée contenant des agents de renforcement, charges ou inserts de longueur réduite, p. ex. filaments coupés, fibres coupées ou crins
Methods and apparatus for determinant assembly manipulation are disclosed. A disclosed apparatus to manipulate a panel component for assembly thereof includes a cam rotatably coupled to a jig, the cam having a first interface portion, and a support frame to hold the panel component, the support frame having a second interface portion to contact the first interface portion in at least one rotational orientation of the cam.
A system configured to assist an operator that is inserting wires into terminal block cavities that are connected to electrical equipment. The system includes a computing device that accesses one or more data tables. The data tables identify the wires and the corresponding terminal block where the wires are to be connected. The computing device is configured to create a plug map based on the one or more data tables. The plug map is a digital visualization that replicates the configuration of terminal blocks. The plug map is configured to be displayed as a graphical user interface on a monitor. During use, the computing device highlights the cavity to enable the operator to connect the wire to the correct terminal block.
H01R 43/00 - Appareils ou procédés spécialement adaptés à la fabrication, l'assemblage, l'entretien ou la réparation de connecteurs de lignes ou de collecteurs de courant ou pour relier les conducteurs électriques
56.
OPERATIONAL SIMULATIONS OF PLANNED MAINTENANCE FOR VEHICLES
Implementations for operational simulations of planned maintenance effects for a plurality of vehicles are provided. One aspect provides a computing system comprising processing circuitry configured to provide a plurality of operational models that comprises a route model, a preparation model, and a planned maintenance model. The processing circuitry is further configured to, using the plurality of operational models, execute an operational simulation that generates interactions between a route simulation and a planned maintenance simulation for a plurality of routes in a route schedule, wherein executing the operational simulation comprises simulating performance of a scheduled maintenance task for a vehicle of the plurality of vehicles and determining an effect of the simulated performance of the scheduled maintenance task on the route simulation. The processing circuitry is further configured to output the effect of the simulated performance.
Methods and apparatus for power generation and/or thermal management on a high speed flight vehicle include circulating a power generation loop working fluid through a power generation loop, which absorbs heat associated with the flight vehicle. A generator operably coupled to the power generation loop generates electrical power. Additionally, a heat transport loop working fluid may circulate through a heat transport loop to provide thermal management through heat transfer.
F01K 7/32 - Ensembles fonctionnels de machines à vapeur caractérisés par l'emploi de types particuliers de machines motricesEnsembles fonctionnels ou machines motrices caractérisés par un circuit de vapeur, un cycle de fonctionnement ou des phases particuliersDispositifs de commande spécialement adaptés à ces systèmes, cycles ou phasesUtilisation de la vapeur soutirée ou de la vapeur d'évacuation pour le réchauffage de l'eau d'alimentation les machines motrices utilisant la vapeur à la pression critique ou hypercritique
F01K 25/10 - Ensembles fonctionnels ou machines motrices caractérisés par l'emploi de fluides énergétiques particuliers non prévus ailleursEnsembles fonctionnant selon un cycle fermé, non prévus ailleurs utilisant des vapeurs particulières ces vapeurs étant froides, p. ex. ammoniac, gaz carbonique, éther
F02C 6/18 - Utilisation de la chaleur perdue dans les ensembles fonctionnels de turbines à gaz à l'extérieur des ensembles eux-mêmes, p. ex. ensembles fonctionnels de chauffage à turbine à gaz
A pressure diffuser to accommodate changes in pressure of a fluid within a fluid supply. The pressure diffuser includes a housing with an interior space and with an inlet and an outlet. A diverting member is positioned within the interior space. The diverting member is configured to divert the fluid within the interior space away from the outlet. An elastic membrane is positioned radially within the interior space between the housing and the diverting member. The elastic membrane is configured to receive the fluid from the diverting member and to expand and contract dependent on a pressure of the fluid.
F15B 1/16 - Accumulateurs utilisant un coussin de gazDispositifs de remplissage de gazIndicateurs ou flotteurs à cet effet avec des moyens de séparation flexibles en forme de tubes
A method controls taxiing of an aircraft. A first laser beam and a second laser beam are emitted from the aircraft using a wavelength configuration. A first backscatter light and a second backscatter light are received at the aircraft in response to emitting the first laser beam and the second laser beam. First backscatter data is generated using the first backscatter light. Second backscatter data is generated using the second backscatter light. A first signal to noise ratio is determined using the first backscatter data. A second signal to noise ratio is determined using the second backscatter data. The wavelength configuration is controlled for the first laser beam and the second laser beam emitted by the lidar system using the first signal to noise ratio and the second signal to noise ratio. A taxiing operation is performed for the aircraft using the first backscatter data and the second backscatter data.
Methods and an induction curing system for curing a composite panel. The induction curing system comprises; a rigid curing tool configured to hold a composite material; a vacuum bagging material sealed to the rigid curing tool; and a dimensional control structure having a lattice and an open casing formed of a rigid material, the lattice positioned within a concavity of the open casing, the dimensional control structure sealed to at least one of the vacuum bagging material or the rigid curing tool.
B29C 35/08 - Chauffage ou durcissement, p. ex. réticulation ou vulcanisation utilisant l'énergie ondulatoire ou un rayonnement corpusculaire
B29C 70/44 - Façonnage ou imprégnation par compression pour la fabrication d'objets de longueur définie, c.-à-d. d'objets distincts utilisant une pression isostatique, p. ex. moulage par différence de pression, avec un sac à vide, dans un autoclave ou avec un caoutchouc expansible
A method and apparatus for distributing a number of utilities. The number of utilities may be coupled between a number of utility sources and a utility fixture. The number of utilities may be coupled between the utility fixture and a mobile system.
B29C 39/02 - Moulage par coulée, c.-à-d. en introduisant la matière à mouler dans un moule ou entre des surfaces enveloppantes sans pression significative de moulageAppareils à cet effet pour la fabrication d'objets de longueur définie, c.-à-d. d'objets séparés
B29C 39/10 - Moulage par coulée, c.-à-d. en introduisant la matière à mouler dans un moule ou entre des surfaces enveloppantes sans pression significative de moulageAppareils à cet effet pour la fabrication d'objets de longueur définie, c.-à-d. d'objets séparés en incorporant des parties ou des couches préformées, p. ex. coulée autour d'inserts ou sur des objets à recouvrir
B29C 39/12 - Fabrication d'objets multicouches ou polychromes
B29C 39/22 - Éléments constitutifs, détails ou accessoiresOpérations auxiliaires
B29C 45/14 - Moulage par injection, c.-à-d. en forçant un volume déterminé de matière à mouler par une buse d'injection dans un moule ferméAppareils à cet effet en incorporant des parties ou des couches préformées, p. ex. moulage par injection autour d'inserts ou sur des objets à recouvrir
B29C 65/70 - Assemblage d'éléments préformésAppareils à cet effet par moulage
B60G 3/14 - Suspensions élastiques pour une seule roue avec un seul bras articulé le bras étant sensiblement parallèle à l'axe longitudinal du véhicule le bras étant rigide
B60G 7/00 - Bras de suspension articulésLeurs accessoires
B64C 1/00 - FuselagesCaractéristiques structurales communes aux fuselages, voilures, surfaces stabilisatrices ou organes apparentés
G05B 19/418 - Commande totale d'usine, c.-à-d. commande centralisée de plusieurs machines, p. ex. commande numérique directe ou distribuée [DNC], systèmes d'ateliers flexibles [FMS], systèmes de fabrication intégrés [IMS], productique [CIM]
G05D 1/00 - Commande de la position, du cap, de l'altitude ou de l'attitude des véhicules terrestres, aquatiques, aériens ou spatiaux, p. ex. utilisant des pilotes automatiques
G05D 3/12 - Commande de la position ou de la direction utilisant la contre-réaction
B23P 21/00 - Machines pour l'assemblage de nombreuses pièces différentes destinées à composer des ensembles, avec ou sans usinage de ces pièces avant ou après leur assemblage, p. ex. à commande programmée
B60P 3/025 - Véhicules adaptés pour transporter, porter ou comporter des charges ou des objets spéciaux l'objet étant une boutique, une cafétéria ou un étalage
An elastomer component comprised of an elastomer material having an air volume fraction (AVF) of greater than 5%, and the elastomer component is a three-dimensional solid. An assembly comprises an outer barrier, at least one elastomer component, and a curable material. A method comprises inserting an elastomer component and a curable material into an outer barrier to form an assembly and heating the assembly.
A fluid reservoir comprises a reservoir body and a passage. The reservoir body is configured to be arranged within an aerodynamic component. The passage is configured to operatively couple the reservoir body to an exterior surface of the aerodynamic component. The passage is further configured to flow fluid from the reservoir body to the exterior surface when a pressure differential exceeds a threshold pressure differential. The threshold pressure differential is a difference between a pressure at a terminal end of the passage and a pressure of an interior of the reservoir body. An apparatus comprises an aerodynamic component and a reservoir. The passage is configured to flow fluid from the reservoir body to the exterior surface when a pressure differential exceeds a threshold pressure differential. A method comprises flowing fluid from a reservoir to an exterior surface of an aerodynamic component at a threshold pressure differential.
Methods of peeling a protective film from the composite material are presented. A second protective film on a second face of the composite material sheet is held against a plurality of gripping points of an end effector. The composite material sheet is positioned at an angle relative to the manufacturing floor using the end effector. A first protective film on a first face of the composite material sheet is gripped by a film removal end effector. The first protective film is peeled away from the first face of the composite material sheet by movement of the film removal end effector.
A method includes obtaining first humidity data indicative of a first humidity value at an origin airport of a flight. The method also includes obtaining second humidity data indicative of a second humidity value at a destination airport. The method also includes determining, based on the first humidity data, a first fuel flow rate adjustment for a first phase of flight from a first altitude of the origin airport to a threshold altitude. The method also includes determining, based on the second humidity data, a second fuel flow rate adjustment for a second phase of flight from the threshold altitude to a second altitude of the destination airport. The method also includes estimating total fuel flow for the flight based on the first fuel flow rate adjustment and the second fuel flow rate adjustment.
A method includes comparing a first field of a first data record to a first field of a second data record to determine a first similarity metric based on a number of single character changes used to convert a value of the first field of the first data record to a value of the first field of the second data record and comparing a second field of the first data record to a second field of the second data record to determine a second similarity metric based on whether the second field of the first data record is identical to a value of the second field of the second data record. The method includes determining an aggregate similarity metric based on at least the first similarity metric and the second similarity metric and assigning the second data record to a calibration reliability group based on the aggregate similarity metric.
A manufacturing system including a manufacturing device that includes one or more integrated sensors. The manufacturing system further includes an edge computing device including an edge device processor configured to receive integrated sensor data measured during production of a manufactured part using the manufacturing device. The edge device processor transmits the integrated sensor data to a remote computing device. During the production of the manufactured part, the edge device processor receives a remote processing result from the remote computing device. The remote processing result includes a quality control result notification. The edge device processor, in response to receiving the quality control result notification, programmatically performs one or more auxiliary measurements of the manufactured part and/or manufacturing device to obtain auxiliary sensor data. The edge device processor outputs the quality control result notification and the auxiliary sensor data to a graphical user interface (GUI) displayed at the edge computing device.
A system includes one or more processors configured to obtain navigation system quality information from multiple data sources. The one or more processors are further configured to generate navigation signal interference map information based on the navigation system quality information. For example, the one more processors may be configured to aggregate, based on one or more parameters, first data from a first data source of the multiple data sources, and identify one or more areas associated with low quality navigation signals based on second data from a second data source of the multiple data sources. A portion of the aggregated first data may be discarded based on the one or more areas to generate the navigation signal interference map information. The one or more processors may also be configured to output the navigation signal interference map information.
Systems, apparatuses, and methods provide for a tool to support components on a common hinge line axis. The tool includes a first pin and a second pin coupled in coaxial alignment with each other, defining the common hinge line axis. A first shouldered hinge pin is slidably disposed on the first pin and a second shouldered hinge pin is slidably disposed on the second pin. The first and second shouldered hinge pins allow translation along the common hinge line axis of the supported components when coupled to the first and second shouldered hinge pins. The first and second pins are disposed within a ball and socket joint, which enables pivotal adjustment of the common hinge line axis while maintaining the first and second pins co-axial to each other during adjustment of the common hinge line axis, to aid fit and assembly of the supported components to a mating structure.
A ceramic matrix composite part and methods of locating a composite ply on a layup tool are presented. A composite ply comprising a fiducial is placed onto the layup tool. A position of the fiducial of the composite ply is determined relative to the layup tool. An actual position of the composite ply on the layup tool is determined. A difference between the actual position of the composite ply and a designed position for the composite ply is determined.
Rapidly generated tooling and methods for rapidly generating tooling for composite layup and cure are presented. A foam block is formed into a tool body with a forming surface having a near net shape. A low CTE material is additively deposited onto the forming surface to form a metal cover
A forming area for automated composite processing and methods of maintaining workability of a ceramic matrix composite material in a forming area are presented. It is determined if a humidity within the forming area is in a desired range. In response to a determination that the humidity is not in the desired range, at least one of a heater or a humidifier is activated by an environmental controller to maintain a desired humidity for forming the ceramic matrix composite material within the forming area.
A method includes determining, based on historical data associated with a reliability group, a model fit metric for each reliability model of a plurality of reliability models. The method also includes selecting a particular reliability model based on the model fit metrics. The method also includes estimating calibration interval parameters for the reliability group based on the particular reliability model. The method also includes generating a calibration interval recommendation for the reliability group based on the calibration interval parameters and a reliability target associated with the reliability group.
C08L 71/00 - Compositions contenant des polyéthers obtenus par des réactions créant une liaison éther dans la chaîne principaleCompositions contenant des dérivés de tels polymères
77.
METHODS FOR DETERMINING LIKELIHOODS OF IGNITION HAZARDS
A method is presented for determining a likelihood of an ignition hazard. The method comprises receiving a current waveform for a lightning strike event at a conductive member that forms an interface with a decomposable member. Material parameter inputs for the conductive member and the decomposable member are received. Based at least on one or more of the received material parameter inputs and an energy from the current waveform, a heating of the decomposable member is resolved, and a quantity of volatiles within the interface volume are determined. A total pressure generation within the interface volume is determined. A probability of ignition hazard by the lightning strike event is output based on a comparison of the total pressure generation and a containment pressure threshold for the interface volume.
A computing device may determine, based on first information identifying one or more maximal cliques in a first connectivity graph, a set of potential cliques in a second connectivity graph that is an updated version of the first connectivity graph. The computing device may determine a set of valid cliques, of the set of potential cliques, in the second connectivity graph and may determine, based on the set of valid cliques, a first set of maximal cliques in the second connectivity graph. The computing device may determine, based on a set of nodes of the second connectivity graph that are not included in the first set of maximal cliques, a second set of maximal cliques in the second connectivity graph. The computing device may determine second information identifying the first set of maximal cliques and the second set of maximal cliques.
H04L 41/12 - Découverte ou gestion des topologies de réseau
H04L 41/082 - Réglages de configuration caractérisés par les conditions déclenchant un changement de paramètres la condition étant des mises à jour ou des mises à niveau des fonctionnalités réseau
A bushing configured to receive a connector to connect engine components within an aircraft to absorb forces during a fan blade out. The bushing includes an outer ring, an inner ring that is positioned within and spaced inward from the outer ring with the inner ring having a central opening sized to receive the connector, and spokes that extend between and connect together the outer ring and the inner ring. One or more of the spokes have a linear shape and one or more of the spokes have a non-linear shape.
B64D 33/02 - Aménagement sur les aéronefs des éléments ou des auxiliaires des ensembles fonctionnels de propulsion, non prévu ailleurs des entrées d'air de combustion
B64D 29/06 - Fixation des nacelles, carénages ou capotages
80.
SYSTEM AND METHOD FOR SUPPORTING A LEADING EDGE OF A WING OF AN AIRCRAFT
A support system is configured to couple a leading edge of a wing to a main body of the wing. The support system includes an extender configured to secure to the leading edge and the main body. The extender is configured to extend and retract. The support system is in a retracted position when the extender is retracted. The support system is in a forward extended position when the extender is extended. The leading edge abuts the main body when the support system is in the retracted position. The leading edge is spaced apart from the main body when the support system is in the forward extended position.
A device includes a housing. a first interface on a first side of the housing, a second interface on a second side of the housing opposite the first side, and circuitry within the housing. The first interface is configured to couple to a multimode receiver (MMR) rack. The second interface is configured to couple to a MMR external to the housing. The circuitry is configured to receive, via the first interface, digital data representing navigation signals received at an antenna. The circuitry is configured to perform time, space and frequency filtering operations using the digital data to generate modified digital data. The circuitry is configured to output modified analog navigation signals, based on the modified digital data, to the MMR via the second interface.
B64C 1/36 - FuselagesCaractéristiques structurales communes aux fuselages, voilures, surfaces stabilisatrices ou organes apparentés adaptés pour recevoir des antennes ou des radômes
B64D 45/00 - Indicateurs ou dispositifs de protection d'aéronefs, non prévus ailleurs
H01Q 1/28 - Adaptation pour l'utilisation dans ou sur les avions, les missiles, les satellites ou les ballons
82.
HYBRID TURBOSHAFT AND SOLID OXIDE FUEL CELL PROPULSION SYSTEM AND RELATED METHODS
Hybrid propulsion systems that utilize liquid natural gas solid oxide fuel cells in a manner practical for use in aircraft that avoid the use of heavy batteries, provide transient response times suitable for use in aircraft, and/or simplify reactant pre-conditioning systems using a compressor and turbine pair operatively coupled to the solid oxide fuel cell. Such hybrid propulsion systems for an aircraft may include a liquid natural gas turboshaft engine, a turbo generator operatively coupled to the turboshaft engine, a liquid natural gas solid oxide fuel cell, and an electric fan. The electric fan may be configured to generate thrust for the aircraft and may be powered by the turbo generator and/or the solid oxide fuel cell. Fuel cell reactants may be pre-conditioned using turboshaft bleed air, and the liquid natural gas may be pre-heated by fuel exhaust from the solid oxide fuel cell.
B64D 27/31 - Aéronefs caractérisés par des groupes moteurs électriques à l'intérieur des ailes ou fixés à celles-ci
B64D 27/355 - Aménagements pour la production, la distribution, la récupération ou le stockage d'énergie électrique à bord utilisant des piles à combustible
H01M 8/1009 - Éléments à combustible avec électrolytes solides avec un des réactifs liquide, solide ou chargé en liquide
H01M 8/12 - Éléments à combustible avec électrolytes solides fonctionnant à haute température, p. ex. avec un électrolyte en ZrO2 stabilisé
83.
AIRFLOW SYSTEM FOR A BUILDING AND METHOD OF USING THE SAME TO PROVIDE CONTAMINATION MITIGATION FOR OCCUPANTS OF THE BUILDING
There is provided an airflow system for a building. The airflow system includes at least one air purification system providing purified air and receiving recirculated air; at least one air supply assembly supplying the purified air from the air purification system to at least one interior airflow space including one or more of, an office cubicle, a conference room, and an auditorium; at least one air return assembly returning the recirculated air from the at least one interior airflow space to the at least one air purification system; directional airstream(s) formed between the air supply assembly and the air return assembly, including first directional airstream(s) forming one or more air barriers between occupants, to provide respiratory isolation, and second directional airstream(s) forming an airflow field around each occupant; and at least one control system controlling the airflow system. The airflow system provides a contamination mitigation for each occupant.
A system for removing a cap seal from a fastener, includes a seal remover including fingers outwardly extending from a base. The fingers include one or more first fingers and one or more second fingers. The one or more first fingers are sized, shaped, or configured differently than the one or more second fingers. Passages are defined between the fingers. The seal remover is configured to be coupled to a distal end of an operative portion of a tool. The tool is configured to be operated to rotate the seal remover in relation to the cap seal so that the fingers remove the cap seal from the fastener. Removed portions of the cap seal are discharged through and out of the passages.
B23P 19/04 - Machines effectuant simplement l'assemblage ou la séparation de pièces ou d'objets métalliques entre eux ou des pièces métalliques avec des pièces non métalliques, que cela entraîne ou non une certaine déformationOutils ou dispositifs à cet effet dans la mesure où ils ne sont pas prévus dans d'autres classes pour assembler ou séparer des pièces
F16B 41/00 - Dispositions contre la perte des boulons, écrous, broches ou goupillesDispositions empêchant toute action non autorisée sur les boulons, écrous, broches ou goupilles
85.
PANELS FOR AIRCRAFT FUSELAGES, AIRCRAFT ASSEMBLIES, AND METHODS FOR PANELS AND AIRCRAFT ASSEMBLIES
A panel comprises a panel interior surface, a foam layer, and a composite layer. A first end of the panel is oriented at a first end angle relative to a foam layer interior surface, wherein the first end angle is not 90 degrees. A foam layer interior surface is operatively arranged at the panel interior surface. The composite layer comprises a composite layer interior surface operatively engaged with the foam layer exterior surface. An aircraft assembly comprises a fuselage and at least a first panel and a second panel. A first end angle of a first panel first end corresponds to a second end angle of a second panel second end, and the first panel first end operatively engages the second panel second end. A method comprising operatively engaging a first panel interior surface of a first panel with a fuselage exterior surface of a fuselage.
A microforge system for additive metallic manufacturing includes a forge barrel with a forge head configured to move in opposite directions within the forge barrel. A metal supply device supplies metal powder into the forge barrel, and one or more inductive heaters inductively heat the metal powder within the forge barrel. The forge head oscillates within the forge barrel while the metal powder is heated and sintered onto a substrate to form a solid metal additive layer. The system may include an inert gas supply device to load inert gas into the forge barrel, allowing the metal powder to be heated and forged without a vacuum chamber. The forge head compacts the metal powder to produce a solid metal additive layer with a wrought microstructure. A translation system moves the forge barrel and inductive heaters transversely relative to the forge head's oscillation.
A panel assembly includes a plurality of panels. Each one of the panels includes a first face sheet, a second face sheet, a truss structure connecting the first face sheet and the second face sheet, and a perimeter edge. The panel assembly also includes a primary splice connector that is connected to the first face sheet and the second face sheet along at least a portion of the perimeter edge of directly adjacent ones of the panels. The primary splice connector includes a heat exchanger.
F28D 15/02 - Appareils échangeurs de chaleur dans lesquels l'agent intermédiaire de transfert de chaleur en tubes fermés passe dans ou à travers les parois des canalisations dans lesquels l'agent se condense et s'évapore, p. ex. tubes caloporteurs
B33Y 80/00 - Produits obtenus par fabrication additive
A fiber laser machine tool includes a mounting plate, a fiber laser probe and a rotary actuator. The mounting plate for mounting the tool to a manufacturing system for vertical and horizontal movement in relation to a honeycomb core structure. The fiber laser probe includes an inner core with a fiber optic conductor. The inner core is installed on the mounting plate to prevent rotation of the center. The probe also includes a rotational outer sheath with a mirror for reflecting laser energy from the fiber optic conductor toward walls of cells in the honeycomb core structure to perforate the walls. The rotary actuator is installed on the mounting plate and includes a shaft linked to the rotational outer sheath to enable rotation of the mirror. Various manufacturing systems and methods for modifying walls of cells in honeycomb core structures are also disclosed.
There is provided a portable conduction welding apparatus for conduction welding of thermoplastic composite parts. The apparatus has a heating system with a first heater assembly and a second heater assembly each having a machined insulation block, a machined heater block, heater element(s), and a thermocouple. The apparatus has a force application and monitoring system with a clamp assembly and a load cell. The apparatus has an indexing assembly to index the first heater assembly and the second heater assembly to the clamp assembly. The apparatus has one or more controllers having one or more power supplies. The apparatus is portable and is configured to weld together at a weldline, a first thermoplastic composite part aligned to the first heater assembly and a second thermoplastic composite part aligned to the second heater assembly, by applying force and conducting heat at the weldline during a thermal welding cycle.
B29C 65/34 - Assemblage d'éléments préformésAppareils à cet effet par chauffage, avec ou sans pressage avec des éléments chauffés qui restent dans le joint, p. ex. un "élément de soudage perdu"
B29C 65/00 - Assemblage d'éléments préformésAppareils à cet effet
B29C 65/78 - Moyens pour la manipulation des éléments à assembler, p. ex. pour la fabrication de récipients ou d'objets creux
90.
AIRFLOW SYSTEM FOR A BUILDING AND METHOD OF USING THE SAME TO PROVIDE CONTAMINATION MITIGATION FOR OCCUPANTS OF THE BUILDING
There is provided an airflow system for a building. The airflow system includes at least one air purification system providing purified air and receiving recirculated air; at least one air supply assembly supplying the purified air from the air purification system to at least one interior airflow space including one or more of, an aisleway, a cafeteria, a restroom, and an elevator; at least one air return assembly returning the recirculated air from the at least one interior airflow space to the at least one air purification system; directional airstream(s) formed between the air supply assembly and the air return assembly, and comprising at least one or more of, a directed airflow field around each occupant, air barrier(s) between each occupant, and an airflow field around each occupant; and at least one control system controlling the airflow system. The airflow system provides a contamination mitigation for each occupant.
F24F 11/72 - Systèmes de commande caractérisés par leurs grandeurs de sortieDétails de construction de tels systèmes pour la commande de l’apport en air traité, p. ex. commande de la pression
F24F 11/30 - Aménagements de commande ou de sécurité en relation avec le fonctionnement du système, p. ex. pour la sécurité ou la surveillance
F24F 13/08 - Organes de réglage de l'écoulement d'air, p. ex. persiennes, grilles, volets ou plaques directrices
F24F 110/65 - Teneur en substances spécifiques ou en contaminants
A dimmable window system includes a reveal retaining a window, a dimmable member, and an energy harvester configured to harvest energy to provide power to the dimmable member and other components of the dimmable window system. The dimmable window system can be configured for a vehicle, such as an aircraft.
Heat exchangers with integrally formed flow turbulators are disclosed. An example heat exchanger includes a plurality of fluid passages forming a fluid flow path through the heat exchanger and a plurality of flow turbulators within the fluid passages, the flow turbulators within the fluid flow path and being integrally formed with a body of the heat exchanger.
F28F 1/40 - Éléments tubulaires ou leurs ensembles avec moyens pour augmenter la surface de transfert de chaleur, p. ex. avec des ailettes, avec des saillies, avec des évidements les moyens étant uniquement à l'intérieur de l'élément tubulaire
Door latching systems, apparatus, articles of manufacture, and methods are disclosed. An example door latch includes a worm gear including a worm wheel and a worm screw, the worm wheel rotatable upon rotation of the worm screw; a lever operatively coupled to the worm wheel, the lever to rotate based on rotation of the worm wheel; a cam surface, the lever to contact the cam surface between a first rotational position and a second rotational position, the second rotational position different from the first rotational position; and a pin to enable rotation of the worm gear.
A system for determining bore characteristics of a hole includes a measuring tool and a controller. The measuring tool is configured to measure a hole and generate data representing the hole. The controller is in communication with the measuring tool and is configured to determine at least one of the bore characteristics based on the data from the measuring tool.
G01B 11/00 - Dispositions pour la mesure caractérisées par l'utilisation de techniques optiques
G01B 11/03 - Dispositions pour la mesure caractérisées par l'utilisation de techniques optiques pour mesurer la longueur, la largeur ou l'épaisseur en mesurant les coordonnées de points
G01B 11/12 - Dispositions pour la mesure caractérisées par l'utilisation de techniques optiques pour mesurer des diamètres des diamètres intérieurs
G01B 11/22 - Dispositions pour la mesure caractérisées par l'utilisation de techniques optiques pour mesurer la profondeur
G01B 11/26 - Dispositions pour la mesure caractérisées par l'utilisation de techniques optiques pour mesurer des angles ou des cônesDispositions pour la mesure caractérisées par l'utilisation de techniques optiques pour tester l'alignement des axes
G01B 11/30 - Dispositions pour la mesure caractérisées par l'utilisation de techniques optiques pour mesurer la rugosité ou l'irrégularité des surfaces
G01D 5/00 - Moyens mécaniques pour le transfert de la grandeur de sortie d'un organe sensibleMoyens 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 déterminéTransducteurs non spécialement adaptés à une variable particulière
G01D 5/26 - Moyens mécaniques pour le transfert de la grandeur de sortie d'un organe sensibleMoyens 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 déterminéTransducteurs non spécialement adaptés à une variable particulière utilisant des moyens optiques, c.-à-d. utilisant de la lumière infrarouge, visible ou ultraviolette
G01D 5/28 - Moyens mécaniques pour le transfert de la grandeur de sortie d'un organe sensibleMoyens 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 déterminéTransducteurs non spécialement adaptés à une variable particulière utilisant des moyens optiques, c.-à-d. utilisant de la lumière infrarouge, visible ou ultraviolette avec déviation des rayons lumineux, p. ex. pour une indication optique directe
G01N 21/954 - Inspection de la surface intérieure de corps creux, p. ex. d'alésages
95.
METHODS FOR MANUFACTURING NON-CRIMP FABRIC AND COMPOSITE STRUCTURES COMPRISING NON-CRIMP FABRIC WITH BINDER, AND PREFORM COMPRISING NON-CRIMP FABRIC WITH BINDER
A method for manufacturing a non-crimp fabric includes providing a plurality of layers of continuous fibers held together by stitch threads and applying a binder between adjacent layers of the plurality of layers of continuous fibers and on an outer layer of the plurality of layers of continuous fibers, wherein the binder has an activation temperature below a melting temperature of the stitch threads.
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 5/06 - Produits stratifiés caractérisés par l'hétérogénéité ou la structure physique d'une des couches caractérisés par les caractéristiques de structure d'une couche comprenant des fibres ou des filaments caractérisés par une couche fibreuse imbriquée ou cousue avec une autre couche, p. ex. de fibres, de papier
B32B 5/22 - 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
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
A computing system is provided, including one or more processing devices configured to receive a manufacturing change specification of a proposed change to a manufacturing system. At a first trained machine learning model, the one or more processing devices are further configured to compute one or more predicted change categories of the proposed change. At a second trained machine learning model, the one or more processing devices are further configured to compute a change magnitude classification associated with the proposed change. The second trained machine learning model is configured to compute the change magnitude classification based at least in part on the one or more predicted change categories. The one or more processing devices are further configured to output the one or more predicted change categories and the change magnitude classification to a user interface.
B64F 5/00 - Tracé, fabrication, assemblage, nettoyage, entretien ou réparation des aéronefs, non prévus ailleursManipulation, transport, test ou inspection de composants d’aéronefs, non prévus ailleurs
A method of forming a dry fiber stack, a carrier encapsulated composite, and a flexible consolidation and forming carrier are presented. The flexible consolidation and forming carrier comprises an integrated heating element arranged in a material support region, a flexible base material encompassing the integrated heating element, and a seal portion around a perimeter of the flexible consolidation and forming carrier.
B29C 35/02 - Chauffage ou durcissement, p. ex. réticulation ou vulcanisation
B29C 70/44 - Façonnage ou imprégnation par compression pour la fabrication d'objets de longueur définie, c.-à-d. d'objets distincts utilisant une pression isostatique, p. ex. moulage par différence de pression, avec un sac à vide, dans un autoclave ou avec un caoutchouc expansible
B29L 31/30 - Véhicules, p. ex. bateaux ou avions, ou éléments de leur carrosserie
A computing system is provided, including one or more processing devices configured to receive a manufacturing change specification of a proposed change to a manufacturing system. At a first trained machine learning model, the one or more processing devices are further configured to compute one or more predicted change categories of the proposed change. At a second trained machine learning model, the one or more processing devices are further configured to compute a change magnitude classification associated with the proposed change. The second trained machine learning model is configured to compute the change magnitude classification based at least in part on the one or more predicted change categories. The one or more processing devices are further configured to output the one or more predicted change categories and the change magnitude classification to a user interface.
A device includes one or more processors configured to generate an operational congestion metric associated with a particular airport, wherein the operational congestion metric is based at least on one or more usage metrics for the particular airport. The one or more processors are configured to generate an impact congestion metric non-linearly based at least on the operational congestion metric. The one or more processors are configured to determine based on the impact congestion metric, a congestion prediction for the particular airport. The one or more processors are configured to communicate a congestion alert for the particular airport, wherein the congestion alert is based at least on the congestion prediction
A system and a method included a control unit configured to receive wind characteristics for locations at and between a current location of an aircraft and an arrival location, and revise a flight plan at one or more of the locations based on the wind characteristics to provide a revised flight plan. The aircraft is configured to be operated to fly from the current location to the arrival location according to the revised flight plan.
