A method for automated cable wire processing includes receiving a set of two or more cable wires, including at least a first cable wire positioned at a selection position, and a second cable wire positioned away from the selection position. A cable selection tool is automatically moved to contact the set of two or more cable wires, such that contact between the cable selection tool and the first cable wire causes a tip portion of the first cable wire to extend into a working region, and contact between the cable selection tool and the second cable wire moves a tip portion of the second cable wire outside of the working region. One or more tip processing operations are applied to the tip portion of the first cable wire within the working region.
A tool is provided for installing a fastener, having a sleeve and a pin threadably received into the sleeve, into an opening of a structure. The tool includes a frame, a clamp mounted to the frame such that the clamp is configured to move longitudinally relative to the frame, the clamp being configured to grab a pintail of the pin of the fastener, a linear actuator operatively connected to the clamp such that the linear actuator is configured to drive linear movement of the clamp relative to the frame, a wrench mounted to the frame such that the wrench is configured to rotate relative to the frame, the wrench being configured to grab the pintail of the pin, and a rotary actuator operatively connected to the wrench such that the rotary actuator is configured to drive rotation of the wrench relative to the frame.
A system and a method include a first communication system onboard an aircraft and a control unit having one or more processors that determine that one or more ambient conditions require a de-icing event of the aircraft, determine a location of the aircraft, and a status of one or more systems of the aircraft. The first communication system establishes a bi-directional communication link with a second communication system of a de-icing system. The first communication system receives one or more command messages from the second communication system indicating a status of the de-icing event. The control unit changes one or more operating settings of the aircraft responsive to completion of the de-icing event
A method of assessing the ability to remove powder from an additively manufacturable article includes performing the following for each of a plurality of discrete starting points distributed within a sampling volume: calculating the starting point directional trajectory lengths of a plurality of trajectories of a particle starting from the starting point and moving in an initial direction respectively along a plurality of combinations of a polar angle ϕ and an azimuthal angle θ of a spherical coordinate system about the starting point, and calculating an average of the starting point directional trajectory lengths to give a starting point average trajectory length for the starting point. The method also includes calculating an average of the starting point average trajectory lengths respectively of the plurality of starting points to give a global average trajectory length for the article.
A container to contain a mobility device during transport on a vehicle. The container has a first side, a second side, and a wheel side. Wheels are connected to the wheel side. The container is selectively positionable between an upright orientation and a side orientation. The upright orientation positions the first side downward to contact a support surface and with the wheels spaced away from support surface. The side orientation comprises the first wheel side positioned downward towards the support surface and with the first side and the second side spaced away from the support surface.
A method is provided for supporting an aircraft approaching a runway on an airfield. The method includes receiving a sequence of images of the airfield, captured by a camera onboard the aircraft approaching the runway. For at least one image of the sequence of images, the method includes applying the image(s) to a machine learning model trained to predict a pose of the aircraft relative to the runway. The machine learning model is configured to map the image(s) to the pose based on a training set of labeled images with respective ground truth poses of the aircraft relative to the runway. The pose is output as a current pose estimate of the aircraft relative to the runway for use in at least one of monitoring the current pose estimate, generating an alert based on the current pose estimate, or guidance or control of the aircraft on a final approach.
G06T 7/73 - Détermination de la position ou de l'orientation des objets ou des caméras utilisant des procédés basés sur les caractéristiques
G06T 3/40 - Changement d'échelle d’images complètes ou de parties d’image, p. ex. agrandissement ou rétrécissement
G08G 5/02 - Aides pour l'atterrissage automatique, c. à d. systèmes dans lesquels les données des vols d'avions arrivant sont traitées de façon à fournir les données d'atterrissage
7.
MULTI-FUNCTION END EFFECTOR AND METHOD FOR TESTING THE ELECTRICAL CONTINUITY BETWEEN A STRUCTURE AND A FASTENER
An end effector has an end effector frame configured to be mounted to a movable platform capable of positioning the end effector relative to a structure. In addition, the end effector has a plurality of process tools mounted to the end effector frame and having different functional capabilities associated with hole formation and fastener installation in the structure. Furthermore, the end effector has a continuity tester configured to determine the existence of an uninterrupted electrical path between a fastener and the structure after installation of the fastener.
G01R 27/02 - Mesure de résistances, de réactances, d'impédances réelles ou complexes, ou autres caractéristiques bipolaires qui en dérivent, p. ex. constante de temps
Technology provides for controlling a high-energy management system for an aircraft that includes receiving sensor data from a plurality of high-energy (HE) systems, wherein each of the plurality of HE systems is located in an aircraft, determining a present state of each of the plurality of HE systems based on the sensor data, determining a target state of each of the plurality of HE systems based on the present state of each of the plurality of HE systems and a set of HE system rules, and automatically generating one or more control actions to effect control of one or more of the plurality of HE systems based on the target state of each of the plurality of HE systems. Examples further include receiving a schedule of tasks to be performed on the aircraft, where determining the target state is further based on the schedule of tasks.
A method for modeling joints with fasteners includes receiving multiple input parameters of multiple components connectable with one or more fasteners; calculating multiple second level parameters with a computer based on the input parameters; building multiple component models of the components absent the one or more fasteners based on the second level parameters; subtracting multiple bolt bores from the component models; and generating an assembly model by combining the component models with one or more fastener models of the one or more fasteners in the bolt bores. The method further includes applying multiple boundary conditions to the assembly model; applying multiple loads to the assembly model under the boundary conditions to generate multiple analysis key words; and generating an input file based on the analysis key words. The input file is suitable for a finite element analysis.
G06F 30/23 - Optimisation, vérification ou simulation de l’objet conçu utilisant les méthodes des éléments finis [MEF] ou les méthodes à différences finies [MDF]
An aircraft wing includes a wing root having a leading edge, a trailing edge, and a distal end. The wing also includes a wing tip and a wing-tip hinge that pivotally couples the wing tip to the wing root and defines a wing-tip axis that is perpendicular to a folding plane. The wing tip is pivotable about the wing-tip axis, within the folding plane, between, and inclusive of, an extended position and a retracted position, relative to the wing root. When in the extended position, the leading edge of the wing tip extends from the leading edge of the wing root in a spanwise direction of the wing root. When in the retracted position, the leading edge of the wing tip extends from the leading edge of the wing root in a chordwise direction of the wing root.
A system includes one or more control units configured to determine one or more fuel consumption models for an aircraft. A method includes determining, by one or more control units, one or more fuel consumption models for an aircraft. A non-transitory computer-readable storage medium comprising executable instructions that, in response to execution, cause one or more control units comprising a processor, to perform operations including determining one or more fuel consumption models for an aircraft.
F02C 9/44 - Commande de l'alimentation en combustible sensible à la vitesse de l'aéronef, p. ex. commande du nombre de Mach, optimisation de la consommation en combustible
B64D 45/00 - Indicateurs ou dispositifs de protection d'aéronefs, non prévus ailleurs
A spray gun assembly for applying a coating with plural components includes a nozzle, a main pneumatic inlet, an atomizing air flow path, a fan air flow path, a colloidal feed inlet, an internal atomizing outlet, a pressurized feed inlet, and a catalyst outlet. The nozzle includes a main atomizing outlet and a fan air outlet. The main pneumatic inlet receives compressed air from a compressed air source. The colloidal feed inlet receives a colloidal suspension component of the coating via gravity feed from a gravity feed container. The pressurized feed inlet receives a catalyst component of the coating from a pressurized feed container. The catalyst outlet expels the catalyst component in the fan air flow path proximate the nozzle. A method for applying a coating with plural components is also provided. A system includes the gravity feed container, the pressurized feed container and the spray gun assembly.
B05C 17/03 - Rouleaux avec un système d'alimentation en matériau à partir d'une source externe
B05B 7/04 - Pistolets pulvérisateursAppareillages pour l'évacuation avec des dispositifs permettant le mélange de liquides ou d'autres matériaux fluides avant l'évacuation
13.
METHODS OF MAKING A REINFORCEMENT PART AND REINFORCING A VEHICLE
A method of making a reinforcement part for a vehicle includes applying a release film directly onto a surface of the vehicle, applying a first metallic layer directly or indirectly onto the release film, applying a curable bonding layer directly onto the first metallic layer, and applying a second metallic layer directly onto the curable bonding layer. The method also includes applying pressure to the first metallic layer, the curable bonding layer, and the second metallic layer so that the first metallic layer, the curable bonding layer, and the second metallic layer are compressed against the surface. The method further includes curing the curable bonding layer when pressure is applied to the curable bonding layer to form the reinforcement part. The method additionally includes, after curing the curable bonding layer, removing the reinforcement part from the surface.
B32B 37/26 - Procédés ou dispositifs pour la stratification, p. ex. par polymérisation ou par liaison à l'aide d'ultrasons caractérisés par les propriétés des couches avec au moins une couche influençant la liaison au cours de la stratification, p. ex. couches anti-adhésives ou couches égalisatrices de la pression
B32B 37/10 - Procédés ou dispositifs pour la stratification, p. ex. par polymérisation ou par liaison à l'aide d'ultrasons caractérisés par la technique de pressage, p. ex. faisant usage de l'action directe du vide ou d'un fluide sous pression
B64F 5/10 - Fabrication ou assemblage d’aéronefs, p. ex. gabarits à cet effet
14.
SYSTEM, METHOD, AND APPARATUS FOR X-RAY BACKSCATTER INSPECTION OF PARTS
Disclosed herein is an x-ray backscatter apparatus for non-destructive inspection of a part. The x-ray backscatter apparatus includes an x-ray source and an x-ray collimator. The x-ray collimator includes a plurality of emission apertures and a detection aperture. The x-ray backscatter apparatus further includes an x-ray intensity sensor that is fixed to the x-ray collimator over the detection aperture such that at least a portion of an uncollimated x-ray emission, collimated into the detection aperture, is detected by the x-ray intensity sensor. The x-ray backscatter apparatus additionally includes an emission alignment adjuster that is operable to adjust a position of the uncollimated x-ray emission relative to the plurality of emission apertures and the detection aperture in response to the at least the portion of the uncollimated x-ray emission detected by the x-ray intensity sensor.
G01N 23/203 - Recherche ou analyse des matériaux par l'utilisation de rayonnement [ondes ou particules], p. ex. rayons X ou neutrons, non couvertes par les groupes , ou en utilisant la diffraction de la radiation par les matériaux, p. ex. pour rechercher la structure cristallineRecherche ou analyse des matériaux par l'utilisation de rayonnement [ondes ou particules], p. ex. rayons X ou neutrons, non couvertes par les groupes , ou en utilisant la diffusion de la radiation par les matériaux, p. ex. pour rechercher les matériaux non cristallinsRecherche ou analyse des matériaux par l'utilisation de rayonnement [ondes ou particules], p. ex. rayons X ou neutrons, non couvertes par les groupes , ou en utilisant la réflexion de la radiation par les matériaux en mesurant la rétrodiffusion
G01N 23/20008 - Détails de construction des appareils d’analyse, p. ex. caractérisés par la source de rayons X, le détecteur ou le système optique à rayons XLeurs accessoiresPréparation d’échantillons à cet effet
H01J 35/14 - Dispositifs de concentration, de focalisation ou d'orientation du rayon cathodique
A data transmission system includes a sensor attached to an aircraft exterior and configured to generate sensor data. An external housing is attached to an exterior portion of an aircraft window. The external housing includes a digital-to-optical convertor configured to convert the sensor data into optical signals. The external housing also includes a transmitting optical device configured to transmit the optical signals through the aircraft window. An internal housing is attached to an interior portion of the aircraft window. The internal housing includes an optical receiver configured to receive the optical signals transmitted through the aircraft window. The internal housing also includes an optical-to-digital convertor configured to convert the optical signals received from the optical receiver into second sensor data. The second sensor data is representative of the detected condition. A data acquisition system internal to the aircraft is configured to receive the second sensor data.
A system includes a power-circulating transmission having a plurality of transmission components arranged in series to circulate motion along a continuous loop and a test article coupled to the power-circulating transmission. The system includes a clutch, a brake, a starting-torque motor, a running motor, and a running-torque motor. The brake selectively couples or decouples the transmission components such that the power-circulating transmission is in an engaged or disengaged power-circulating state. The brake selectively inhibits motion of one of the transmission components when the power-circulating transmission is in the disengaged power-circulating state. The starting-torque motor applies a static torque load to the power-circulating transmission. The running motor applies power to the power-circulating transmission to drive the motion along the continuous loop. The running-torque motor applies a dynamic torque load to the power-circulating transmission.
An aircraft cooling system comprises an evaporator, condenser, an accumulator, and a pump system. The evaporator is configured to cool a set of heat loads in an aircraft using a liquid. The liquid forms a vapor in response to cooling the set of heat loads. The condenser is configured to receive the vapor from the evaporator and cool the vapor in which cooling the vapor forms the liquid. The accumulator is configured to receive the liquid from the condenser and store the liquid. The pump system is configured to pump the liquid stored in the accumulator to the evaporator.
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
B64D 33/08 - Aménagement sur les aéronefs des éléments ou des auxiliaires des ensembles fonctionnels de propulsion, non prévu ailleurs des systèmes de refroidissement des ensembles fonctionnels de propulsion
F28D 21/00 - Appareils échangeurs de chaleur non couverts par l'un des groupes
H01M 8/04007 - Dispositions auxiliaires, p. ex. pour la commande de la pression ou pour la circulation des fluides relatives à l’échange de chaleur
H01M 8/10 - Éléments à combustible avec électrolytes solides
H02K 7/18 - Association structurelle de génératrices électriques à des moteurs mécaniques d'entraînement, p. ex. à des turbines
H05K 7/20 - Modifications en vue de faciliter la réfrigération, l'aération ou le chauffage
20.
Configuration for a LH2 Fuel Cell Aircraft with Distributed Systems
An aircraft comprises a fuselage, wings connected to the fuselage, engines connected to the wings, and liquid hydrogen tanks. Each engine in the engines comprises a nacelle, an electric motor within the nacelle, a fuel cell stack within the nacelle, and a nacelle heat exchanger within the nacelle that receives air flowing through an inlet in the nacelle. The liquid hydrogen tanks are configured to store liquid hydrogen, wherein the liquid hydrogen tanks extend along an outside of the fuselage and above the wings and below windows in the fuselage.
B64D 37/04 - Disposition de ceux-ci à l'intérieur ou sur les aéronefs
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
B64D 33/08 - Aménagement sur les aéronefs des éléments ou des auxiliaires des ensembles fonctionnels de propulsion, non prévu ailleurs des systèmes de refroidissement des ensembles fonctionnels de propulsion
Mid-air collision (MAC) risk models and systems and methods for generating MAC risk maps are disclosed. An example apparatus disclosed herein includes at least one processor circuit to determine a horizontal distance and a vertical distance between a grid location in an airspace and a point of a flight trajectory, the flight trajectory associated with an encounter event with respect to the grid location, determine a first overlap probability between (a) a first horizontal probability distribution corresponding to the grid location and (b) a second horizontal probability distribution corresponding to the point, the second horizontal probability distribution corresponding to the horizontal distance, determine a second overlap probability between (c) a first vertical probability distribution corresponding to the grid location and (d) a second vertical probability distribution corresponding to the point, the second vertical probability distribution corresponding to the vertical distance, determine, based on the first overlap probability and the second overlap probability, a risk metric corresponding to the grid location, and generate a risk map based on the risk metric.
Apparatus and methods are provided for fabrication of a structure, for example, a half barrel section of a fuselage. The apparatus includes an indexing unit dimensioned for coupling to an indexing feature disposed on the structure. The structure proceeds along a process direction during fabrication. A cutting station cuts out manufacturing excess from the structure to form, for example, openings for windows and doors. A method for fabrication of a structure includes indexing a structure to a cutting station based on an indexing feature associated or located on the structure. The method includes operating the cutting station to cut manufacturing excess from the structure. A method includes removing cut sections of the manufacturing excess and routing these sections away from the cutting station.
Thresholds for flooring in an aircraft are described herein. An example aircraft includes a subfloor, first flooring material on the subfloor, second flooring material on the subfloor, and a threshold at least partially between the first flooring material and the second flooring material. The threshold includes a vertical body portion having a top surface, a bottom surface, a first side surface, and a second side surface. The vertical body portion has a concave area extending into the second side surface at the bottom surface, and wherein a second edge of the second flooring material extends into the concave area. The threshold also includes a ramp portion extending from the first side surface. The ramp portion has a decreasing thickness from the vertical body portion to a distal end of the ramp portion. The ramp portion is positioned between a portion of the first flooring material and the subfloor.
B32B 3/08 - Caractérisés par des caractéristiques de forme en des endroits déterminés, p. ex. au voisinage des bords caractérisés par des éléments ajoutés à des endroits déterminés
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 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
B32B 27/30 - Produits stratifiés composés essentiellement de résine synthétique comprenant une résine vinyliqueProduits stratifiés composés essentiellement de résine synthétique comprenant une résine acrylique
B32B 27/40 - Produits stratifiés composés essentiellement de résine synthétique comprenant des polyuréthanes
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
24.
FULLY-AUTOMATED GENERATION OF FIXED-ANGLE ADDENDUMS FOR USE WITH SHEET FORMING MANUFACTURING
A computer-implemented method of generating an addendum surface for use in forming a sheet metal part by using an Incremental Sheet Forming (ISF) manufacturing process, wherein the method includes: providing a Computer Aided Design (CAD) geometry of the sheet metal part to be formed; and generating an addendum surface that surrounds and extends the CAD geometry; wherein the addendum surface has a constant slope everywhere and has no regions of self-intersection. The addendum surface can be used to manufacture a male and/or a female underform tool for use in the ISF process, such as Two-Point Incremental Forming (TPIF). The addendum surface has a user-specified constant design wall angle, θc, which can be selected to prevent tearing of sheet metal parts during ISF due to excessive thinning at large wall angles (i.e., wall angles greater than 60°).
A jig for forming holes in a workpiece includes a body. The body includes a first jig-surface and a second jig-surface. The first jig-surface includes a jig-surface contour. The jig-surface contour is complementary to a workpiece-surface contour of a workpiece-surface of the workpiece. The second jig-surface is planar and opposite to the first jig-surface. The jig includes through holes that extend through the body between the first jig-surface and the second jig-surface for forming holes in the workpiece. Each one of the through holes includes a through-hole axis that is perpendicular to the second jig-surface and that is non-perpendicular to the first jig-surface such that each one of the holes formed in the workpiece has a hole axis that is non-perpendicular to the workpiece-surface.
A thermal detection assembly includes a housing extending between a first end and a second end. The first end of the housing being operably coupled with a surface of a power system and the housing extending through a passage of the surface. The housing includes interior surfaces defining a cavity that has an opening proximate the second end of the housing. An indicator device is disposed within the cavity and is engaged with a thermal spring system. Characteristics of the thermal spring system change responsive to being exposed to a temperature exceeding a designated threshold. The thermal spring system controls movement of the indicator device to move the indicator device from a first position to a second position responsive to the characteristics changing. A portion of the indicator device moves out of the cavity responsive to the thermal spring system moving the indicator device to the second position.
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 heat exchanger system for an aircraft comprises nacelle having an inlet and an outlet, a nacelle heat exchanger within the nacelle, and a fan system within the nacelle. Air flows into the nacelle through the inlet and out of the nacelle through the outlet. The nacelle heat exchanger is configured to transfer heat away from a coolant using the air in an airflow to the nacelle heat exchanger. The fan system is configured to increase the airflow to the nacelle heat exchanger.
B64C 3/36 - Structures adaptées pour réduire les effets de l'échauffement aérodynamique ou les effets d'un échauffement externe d'une autre origine
F02K 3/06 - Ensembles fonctionnels comportant une turbine à gaz entraînant un compresseur ou un ventilateur soufflant dans lesquels une partie du fluide énergétique passe en dehors de la turbine et de la chambre de combustion l'ensemble fonctionnel comprenant des soufflantes carénées, c.-à-d. des soufflantes à fort débit volumétrique sous basse pression pour augmenter la poussée, p. ex. du type à double flux comprenant une soufflante avant
29.
Liquid Hydrogen Feed System for Fuel Cell Powered Aircraft
An aircraft comprises a fuselage; wings; engines connected to the wings; a set of liquid hydrogen tanks; a vent located on the tail on the fuselage; a conduit system connecting the liquid hydrogen tanks to the vent; and a controller. The controller is configured to control the conduit system to remove gaseous hydrogen in the set of liquid hydrogen tanks to travel through the conduit system and exit at the vent in response to pressure in the set of liquid hydrogen tanks being greater than a specified tolerance.
B64D 27/355 - Aménagements pour la production, la distribution, la récupération ou le stockage d'énergie électrique à bord utilisant des piles à combustible
30.
Start-Up of High Temperature Proton Exchange Membrane (HTPEM) Fuel Cell Aircraft with Multiple Power Generating Units
Aircraft comprises a heater system, a conduit system thermally connected to fuel cell stacks, a pump system, and a controller. The heater system is configured to heat a coolant. The coolant flows through the conduit system. The pump system is configured to circulate the coolant through the conduit system to the fuel cell stacks. The controller is configured to control the heater system to heat the coolant to form a heated coolant. The controller is configured to control the pump system to circulate the heated coolant through the conduit system. The controller is configured to control the conduit system to circulate the heated coolant to a subset of the fuel cell stacks, wherein the heated coolant causes the subset of the fuel cell stacks to reach an operating temperature.
B64D 13/08 - Aménagements ou adaptations des appareils de conditionnement d'air pour équipages d'aéronefs, passagers ou pour emplacements réservés au fret l'air étant climatisé l'air étant réchauffé ou refroidi
B60L 50/72 - Détails de construction des piles à combustible spécialement adaptées aux véhicules électriques
B60L 58/33 - Procédés ou agencements de circuits pour surveiller ou commander des batteries ou des piles à combustible, spécialement adaptés pour des véhicules électriques pour la surveillance et la commande des piles à combustible pour la commande de la température des piles à combustible, p. ex. en commandant la charge électrique par refroidissement
B64D 13/00 - Aménagements ou adaptations des appareils de conditionnement d'air pour équipages d'aéronefs, passagers ou pour emplacements réservés au fret
H01M 8/04007 - Dispositions auxiliaires, p. ex. pour la commande de la pression ou pour la circulation des fluides relatives à l’échange de chaleur
H01M 8/04029 - Échange de chaleur par des liquides
31.
Low Temperature Proton Exchange Membrane Charge Air Heat Exchanger
An aircraft air management system comprises an air heat exchanger; an intercooler; and a conduit system connected to the air heat exchanger, the intercooler, and a fuel cell stack. Heated air flows through the conduit system to the air heat exchanger. The air heat exchanger is configured to cool the heated air to form cooler air, wherein the cooler air flows from the air heat exchanger through the conduit system to the intercooler; and the intercooler is configured to cool the cooler air to form cooled air, wherein the cooled air flows from the intercooler through the conduit system to the fuel cell stack.
B64D 13/08 - Aménagements ou adaptations des appareils de conditionnement d'air pour équipages d'aéronefs, passagers ou pour emplacements réservés au fret l'air étant climatisé l'air étant réchauffé ou refroidi
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 8/04014 - Échange de chaleur par des fluides gazeuxÉchange de chaleur par combustion des réactifs
An aircraft thermal management system comprising a high temperature loop and a low temperature loop. The high temperature loop is configured to manage a temperature of a fuel cell stack in a nacelle using a nacelle heat exchanger. The low temperature loop is configured to cool a number of heat loads in a nacelle using a heat capacity of liquid hydrogen.
B64D 37/34 - Conditionnement du carburant, p. ex. réchauffage
B64D 13/06 - Aménagements ou adaptations des appareils de conditionnement d'air pour équipages d'aéronefs, passagers ou pour emplacements réservés au fret l'air étant climatisé
B64D 13/08 - Aménagements ou adaptations des appareils de conditionnement d'air pour équipages d'aéronefs, passagers ou pour emplacements réservés au fret l'air étant climatisé l'air étant réchauffé ou refroidi
An insulation blanket assembly for use on an aircraft includes a cover. The cover has an inboard material and an outboard material. The insulation blanket assembly also includes an insulation material between the inboard material and the outboard material. The insulation blanket assembly also includes one or more support rails attached to at least one of the cover or the insulation material. When the insulation blanket assembly is attached to the aircraft, the one or more support rails are configured to provide separation between an aircraft structure and the insulation material to reduce or eliminate moisture from transferring to the insulation material.
Thermoplastic composite material structures comprise a multi-region thermoplastic surfacing film layer that further comprises first and second regions within the multi-region thermoplastic surfacing film layer having visually-detectable colors different from one another to facilitate surfacing film layer processing, and processing of the thermoplastic composite material stack.
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
B32B 27/28 - Produits stratifiés composés essentiellement de résine synthétique comprenant des copolymères de résines synthétiques non complètement couverts par les sous-groupes suivants
B32B 37/18 - Procédés ou dispositifs pour la stratification, p. ex. par polymérisation ou par liaison à l'aide d'ultrasons caractérisés par les propriétés des couches toutes les couches existant et présentant une cohésion avant la stratification impliquant uniquement l'assemblage de feuilles ou de panneaux individualisés
The present disclosure provides systems and techniques for image-based target detection and tracking. An example technique includes obtaining a geodetic motion-compensated integrated (GMCI) output image of a target. An approximation to a matched filter is generated, based on information associated with the target. An enhanced image is generated based at least in part on the approximation and the GMCI output image. The target is detected and tracked using the enhanced image.
A method forms a multi-ply laminate. A first cutting system cuts and moves a first group of courses into staging positions. Placement robots pick up and place the first group of courses from the staging positions to a layup surface to form a first ply of the multi-ply laminate, changing an orientation of fibers from an initial orientation to a desired orientation for the first ply. A second cutting system cuts and moves a second group of courses into the staging positions while the placement robots are picking up and placing the first group of courses. The placement robots pick up and place the second group of courses from the staging positions to the layup surface to form a second ply of the multi-ply laminate after the first ply has been formed, changing the orientation of the fibers from the initial orientation to the desired orientation for the second ply.
B32B 38/18 - Manipulation des couches ou du stratifié
B32B 5/12 - Produits stratifiés caractérisés par l'hétérogénéité ou la structure physique d'une des couches caractérisés par les caractéristiques de structure d'une couche comprenant des fibres ou des filaments caractérisés par la disposition relative des fibres ou filaments des couches adjacentes
B32B 37/18 - Procédés ou dispositifs pour la stratification, p. ex. par polymérisation ou par liaison à l'aide d'ultrasons caractérisés par les propriétés des couches toutes les couches existant et présentant une cohésion avant la stratification impliquant uniquement l'assemblage de feuilles ou de panneaux individualisés
B32B 38/00 - Opérations auxiliaires liées aux procédés de stratification
B32B 41/00 - Dispositions pour le contrôle ou la commande des procédés de stratificationDispositions de sécurité
37.
Auto Create a Space Reservation for a Customer Configuration Layout
Creating a customer layout configuration of a vehicle is provided. The method comprises pulling, from a customer database, a number of text documents that specify a customer's preferences for the layout configuration. Technical requirements are determined according to a requirement database tool based on the customer preferences. Functional data and logical data are determined according to a system architecture modeling tool based on the customer preferences. A physical layout model of the vehicle is generated according to the customer preferences in the text documents within constraints of the technical requirements, functional data, and logical data.
A computing device, method and computer program product are provided to identify a feature. In a method, images are captured at different points in time and space and a reference plane is defined in a reference frame. The method includes applying image warping to map a plurality of reference points of a respective image in a sensor plane to corresponding reference points of the reference plane and mapping pixel coordinates for a plurality of pixels of the reference plane to the respective image based upon a positional relationship between the reference plane and a representation of the respective image established by having applied image warping to the respective image. The method further includes interpolating from pixels of the respective image to pixels at the pixel coordinates of the reference plane to generate an interpolated representation of the respective image that is then used to identify the feature within the scene.
A deployable panel is provided comprising a first subpanel, a second subpanel, and a shape memory alloy hinge connecting the subpanels. The shape memory alloy hinge enables the subpanels to move between a position in which the first and second subpanels are folded over each other and an unfolded position in response to an energy source that changes the shape of the shape memory alloy hinge, wherein the unfolded position is trained into the shape memory alloy hinge to ensure precise kinematic mating between the subpanels. Shape memory alloy springs are connected to the first subpanel and respective tethers connect the shape memory alloy springs to the second subpanel. The shape memory alloy springs contract in response to a second energy source to pull the subpanels together via the tethers when the subpanels are in the unfolded position to produce a seamless, featureless surface of the deployable panel.
F03G 7/06 - Mécanismes produisant une puissance mécanique, non prévus ailleurs ou utilisant une source d'énergie non prévue ailleurs utilisant la dilatation ou la contraction des corps produites par le chauffage, le refroidissement, l'humidification, le séchage ou par des phénomènes similaires
B64G 1/44 - Aménagements ou adaptations des systèmes fournissant l'énergie utilisant des radiations, p. ex. panneaux solaires déployables
An aircraft wing includes a center wing section having a continuous structure that spans beyond a first side of an aircraft fuselage and beyond a second side of the aircraft fuselage. The aircraft wing also includes a first outboard wing section attached to a first end of the center wing section by a first truss system that is accessible via a first closeout panel. The first end of the center wing section in on the first side of the aircraft fuselage. The aircraft wing also includes a second outboard wing section attached to a second end of the center wing section by a second truss system that is accessible via a second closeout panel. The second end of the center wing section is on the second side of the aircraft fuselage.
There is provided a support pin assembly for full size determinant assembly of an aircraft structure. The support pin assembly includes a clevis having a clevis body with a first clevis lug and a second clevis lug, the clevis configured for mounting to an assembly jig. The support pin assembly further includes a first bushing disposed within the first clevis lug, a second bushing disposed within the second clevis lug, and a pin slideably disposed within the first bushing and the second bushing. The pin includes a shoulder portion with a pin groove, and a part support portion configured to fit through a hole in a part of the aircraft structure. The support pin assembly further includes a sleeve bushing slideably disposed over the part support portion, a retainer element coupled to the part support portion, and a gauge assembly configured for coupling to the pin groove.
A method of obtaining a measurement of a part using depth data from a plurality of sensors comprises obtaining first depth data of a monument and a part from a first sensor and second depth data of the monument and the part from a second sensor. A plurality of planes is detected in the first depth data and the second depth data. Each plane of the plurality of planes corresponds to a corresponding face on the monument. The method comprises performing a rotational alignment of the plurality of planes. The method further comprises performing a translational alignment of the rotationally aligned plurality of planes. One or more transformations are determined that align the first depth data and the second depth data to a common coordinate system based upon the rotational alignment and the translational alignment. A measurement of the part is determined based upon aligned depth data.
A leak detection system and method or an internal cabin of a vehicle include a sensing device configured to detect one or both of water flow or water pressure within a water delivery conduit that is configured to deliver water to one or more water-drawing components within one or more areas of the internal cabin. The sensing device is configured to detect one or both of the water flow or the water pressure into the one or more water-drawing components. A control unit is in communication with the sensing device. The control unit is configured to monitor one or both of the water flow or the water pressure as detected by the sensing device, and determine a presence of a leak in relation to the one or more water-drawing components based on one or both of the water flow or the water pressure.
A system and a method include one or more first spring assemblies and one or more second spring assemblies. Each first spring assembly includes a first spring housing including a first pocket, a first spring disposed within the first pocket, and a first pin disposed within the first pocket and extending from the first pocket. The first pins engage a surface of a body of a latch receiver to control a position of the body of the latch receiver. Each second spring assembly includes a second spring housing including a second pocket, a second spring disposed within the second pocket, and a second pin disposed within the second pocket and extending from the second pocket. The second pins engage a surface of a body of a latch pin to control a position of the body of the latch pin.
There is provided a support pin assembly for full size determinant assembly of an aircraft structure. The support pin assembly includes a block having a vertical bore and a horizontal bore; a bushing within the horizontal bore; a barrel nut having a cylindrical body within the vertical bore and a barrel nut hole; and a pin. The pin includes an insertion portion within the bushing, an interface element, and an extending portion having at least one protruding circumferential portion having two or more flat surface portions on opposing sides to enable rotation of the pin. The at least one protruding circumferential portion is positioned within a hole in a frame section of the aircraft structure, and provides nominal adjustment of the pin, so that with any binding condition of the pin, the pin is released by rotating the pin via the two or more flat surface portions.
A method for manufacturing a wrought metallic article from a metallic-powder composition includes steps of: consolidating the metallic-powder composition to yield a consolidated preform having a cross-sectional area and a relative density of less than 100 percent; reducing the cross-sectional area of the consolidated preform via at least one forming pass of one of a cogging process and a rotary incremental forming process, thereby yielding an intermediate preform; and reducing the cross-sectional area of the intermediate preform via at least one forming pass of another of the cogging process and the rotary incremental forming process.
B22F 3/17 - Fabrication de pièces ou d'objets à partir de poudres métalliques, caractérisée par le mode de compactage ou de frittageAppareils spécialement adaptés à cet effet par forgeage
A net zero power communications system comprising a laser beam generator, a black body, a cooled cavity, an optical absorber in the cooled cavity, and a controller. The controller is configured to identify information for transmission. The controller is configured to control the laser beam generator to emit laser beam pulses at the optical absorber layer that changes a temperature of the optical absorber layer with a pattern that causes the optical absorber layer to emit black body radiation from the cooled cavity to thereby encode the information.
A sealing assembly and associated shaft assembly is disclosed. The sealing assembly comprises a primary seal at a sealing interface between a first sealing face of a first seal ring and a second sealing face of a second seal ring. The sealing assembly also comprises a secondary seal between an extension member of a resilient flexible seal and a second circumferential surface of the second seal ring. The resilient flexible seal is coupled to the first seal ring. The first seal ring is rotatable, relative to the second seal ring, and the extension member is configured to disengage from the second circumferential surface of the second seal ring when the first seal ring is rotating, relative to the second seal ring, at or above a threshold speed.
F16J 15/3284 - Joints d'étanchéité entre deux surfaces mobiles l'une par rapport à l'autre par joints élastiques, p. ex. joints toriques caractérisés par leur structureEmploi des matériaux
49.
SYSTEM AND METHOD FOR PRODUCING MATERIAL PARTICLES
A system for system for producing a plurality of material particles comprises a plated polymer sheet that includes a polymer sheet having a layer of material deposited thereon by electroless plating. The system further comprises a pair of meshing rollers through which the plated polymer sheet is fed, the meshing rollers having a plurality of gear teeth sized and configured to impart a bend of a predetermined radius R in the plated polymer sheet to cause fracturing of the layer of material plated on the polymer sheet. The system further comprises a fluid spray applicator configured to direct fluid flow impinging the plated polymer sheet exiting the meshing rollers to cause separation of the fractured layer of material from the polymer sheet to yield a plurality of material particles.
B22F 9/04 - Fabrication des poudres métalliques ou de leurs suspensionsAppareils ou dispositifs spécialement adaptés à cet effet par des procédés physiques à partir d'un matériau solide, p. ex. par broyage, meulage ou écrasement à la meule
A thin, lightweight control surface is fabricated by induction consolidation of thermoplastic components. The control surface includes a forward section co-consolidated with a rear section. The front section includes a cover and the rear section includes a truss core covered by an outer skin.
Stamp-forming a composite assembly includes applying a low-melt film on an interface surface of at least one spar, loading the spar onto at least one tooling segment such that the interface surface is exposed, and heating the tooling segment to a first temperature that is above a crystallization temperature of the low-melt film and below a melt temperature of a resin of the spar. A second low-melt film may be applied on a fiber-reinforced thermoplastic skin blank, and the skin blank is heated to a second temperature above a melt temperature of a resin of the skin blank. The skin blank is then draped around the tooling segment such that at least some of any second low-melt film contacts the low-melt film on the interface surface of the spar. The stamp press is then closed to co-consolidate the skin blank and the spar, thereby stamp-forming the composite assembly.
B29C 35/08 - Chauffage ou durcissement, p. ex. réticulation ou vulcanisation utilisant l'énergie ondulatoire ou un rayonnement corpusculaire
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, an apparatus, and an aircraft may include a hose reel configured to attach to a first end of a hose, wherein the hose may be further configured to wrap around the hose reel, and wherein the hose reel may be configured to spin. A drogue may be configured to attach to a second end of the hose. At least one spring coupled to the hose reel may be configured to provide a constant force, wherein the hose reel spins in a first direction to allow the hose to protract when the drogue receives a first force that is greater than the constant force of the at least one spring, and wherein the hose reel spins in a second direction to allow the hose to retract when the drogue receives a second force that is less than the constant force of the at least one spring.
B64D 39/02 - Dispositifs permettant de dérouler et d'enrouler les tuyauteries
B65H 75/42 - Noyaux, gabarits, supports ou pièces de tenue pour matériau bobiné, enroulé ou plié, p. ex. tourets, broches, bobines, tubes à cannette, boîtes spécialement adaptés ou montés pour stocker, dérouler de façon répétée et stocker à nouveau des longueurs de matériau prévues pour des buts particuliers, p. ex. tuyaux souples à poste fixe, câbles de force impliquant l'utilisation d'un noyau ou d'un gabarit intérieur formant support pour le paquet de matériau stocké mobile ou transportable fixé à des outils ou machines mobiles ou en faisant partie
B65H 75/48 - Dispositifs automatiques de restockage
Example implementations relate to seat covers and techniques for using such seat covers to partially cover and protect aisle seats on airplanes, buses, trains, and within other venues. An example seat cover for partially covering a seat includes a headrest cover configured to extend over a headrest of the seat, an armrest cover configured to extend over an armrest of the seat positioned proximate the aisle of the vehicle. The armrest cover includes a side surface that extends from the armrest of the seat to a position below a seat cushion of the seat when the seat cover is used to partially cover the seat. The seat cover also includes a side cover portion coupling together the headrest cover and the armrest cover, wherein the side cover portion is configured to extend along a side of a seat back of the seat.
A restart assembly for an automated fiber placement head is presented. The restart assembly for the automated fiber placement head comprises a plurality of pneumatic cylinders, each pneumatic cylinder of the plurality of pneumatic cylinders comprising an extendable piston rod; a plurality of restart rollers, each restart roller of the plurality of restart rollers connected to a respective extendable piston rod of the plurality of pneumatic cylinders, a rotational axis of each restart roller of the plurality of restart rollers perpendicular to the respective extendable piston rod connected to the restart roller.
One example provides a method of evaluating a training performance of a training subject and performed in a training environment. The method receives a simulation state update from a computing system of the training environment, and queries a behavioral elicitation event (BEE) database to determine a set of active BEEs based upon the simulation state update. The method further receives a plurality of simulation action notifications from the computing system, and for each simulation action notification, determines whether an action represented by the simulation action notification matches an elicited action for an active BEE. The method further stores information regarding the elicited action as a response to the active BEE. The method determines a set of completed BEEs comprising any active BEEs that have all corresponding elicited actions met, and for each completed BEE, stores information regarding the completed BEE.
A system and a method include a crank pivotally coupled to a bracket of a main body of a wing of an aircraft. A drive link is pivotally coupled to the crank. A flap link is pivotally coupled to a carrier beam extending from a flap moveably coupled to the main body of the wing. A rocker bracket is pivotally coupled to the flap link and the drive link.
A method to fabricate a composite part includes identifying an out-of-tolerance inconsistency in a current ply of the layup for the composite part and depositing a replacement tow onto the substrate to rework the out-of-tolerance inconsistency in the current ply for the layup of the composite part. In another example, the method includes depositing tows onto a substrate using a multi-lane automated fiber placement device to form a first ply; after out-of-tolerance inconsistencies in the first ply are identified, depositing replacement tows to rework the out-of-tolerance inconsistencies using a single-lane automated fiber placement device; and depositing additional tows onto the substrate using the multi-lane automated fiber placement device to form a second ply overlaying the first ply. A system for fabricating a layup for a composite part includes the multi-lane automated fiber placement device and the single-lane automated fiber placement device.
Methods, Systems, and Apparatus for coordinating drones to communicate with reduced signal to noise, harvest energy, provide camouflage, provide decoying, or provide protective shielding.
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
B64C 39/02 - Aéronefs non prévus ailleurs caractérisés par un emploi spécial
B64U 80/70 - Transport ou stockage spécialement adaptés aux véhicules aériens sans pilote dans des réceptacles
B64U 101/00 - Véhicules aériens sans pilote spécialement adaptés à des utilisations ou à des applications spécifiques
B64U 101/15 - Véhicules aériens sans pilote spécialement adaptés à des utilisations ou à des applications spécifiques à la guerre conventionnelle ou électronique
B64U 101/20 - Véhicules aériens sans pilote spécialement adaptés à des utilisations ou à des applications spécifiques à l’utilisation en tant que relais de communication, p. ex. plates-formes de haute altitude
B64U 101/30 - Véhicules aériens sans pilote spécialement adaptés à des utilisations ou à des applications spécifiques à l’imagerie, à la photographie ou à la vidéographie
A vehicle includes an internal cabin having a main deck cargo compartment, and a barrier system within the internal cabin. The barrier system includes one or more flexible drapes moveable between an open position and a closed position. The barrier system is configured to selectively open and close the main deck cargo compartment from one more other areas of the internal cabin, and/or selectively open and close the main deck cargo compartment into separate areas.
An adjustable gain antenna including an RF emitter configured to emit an RF signal along an emitter axis. A first refractive lens having an optical axis collinear with the emitter axis and a second refractive lens having an optical axis collinear with the emitter axis with the first refractive lens located between the RF emitter and the second refractive lens. A drive mechanism mechanically linked to the first refractive lens and the second refractive lens, wherein the drive mechanism is configured to move the first refractive lens and the second refractive lens longitudinally along the emitter axis to vary a gain of the RF emitter.
H01Q 19/06 - Combinaisons d'éléments actifs primaires d'antennes avec des dispositifs secondaires, p. ex. avec des dispositifs quasi optiques, pour donner à une antenne une caractéristique directionnelle désirée utilisant des dispositifs de réfraction ou de diffraction, p. ex. lentilles
H01Q 3/12 - Dispositifs pour changer ou faire varier l'orientation ou la forme du diagramme de directivité des ondes rayonnées par une antenne ou un système d'antenne utilisant un mouvement mécanique relatif entre des éléments actifs primaires et des dispositifs secondaires des antennes ou systèmes d'antennes
61.
MULTI-SPECTRAL REFERENCE FOR MULTI-SENSOR CALIBRATION
Disclosed herein is an unpowered calibration tool, a system, and a method for performing multi-sensor calibration. An unpowered calibration tool includes a plurality of geometric objects disposed adjacent to each other, the geometric objects are configured to be perceived in one of two different ways for a first type of sensor and one of two different ways for a second type of sensor.
Disclosed herein is calibration tool, system, and method for performing multi-sensor calibration. A sensor system calibration tool includes a plurality of geometric objects disposed adjacent to each other, the geometric objects are configured to be perceived in one of two different ways for a first type of sensor and one of two different ways for a second type of sensor.
G01J 5/00 - Pyrométrie des radiations, p. ex. thermométrie infrarouge ou optique
G01J 5/061 - Dispositions pour éliminer les effets des radiations perturbatricesDispositions pour compenser les changements de la sensibilité par commande de la température de l’appareil ou de ses parties constitutives, p. ex. par des moyens de refroidissement ou par des thermostats
A twist-lock connector for coupling sections of a system for conveying gas includes a socket connector and a fitting connector. The socket connector includes a socket twist-lock. The fitting connector includes a fitting twist-lock. The socket connector receives the fitting connector to engage the fitting twist-lock and the socket twist-lock together by rotating the fitting connector about a connector axis relative to the socket connector.
F16L 37/252 - Accouplements du type à action rapide dans lesquels l'assemblage est réalisé par insertion selon l'axe d'un organe dans l'autre organe et en le faisant tourner d'une amplitude limitée, p. ex. comme dans un raccord à baïonnette dans lesquels l'accouplement et le tuyau sont coaxiaux la partie mâle étant munie sur son pourtour de tenons qui pénètrent dans des encoches correspondantes aménagées dans la partie femelle
F16L 19/025 - Extrémités de tuyaux pourvues de colliers ou de brides formant corps ou non avec les tuyaux, maintenues en contact par un organe vissé les colliers ou les brides formant partie intégrante des extrémités du tuyau
12 - Véhicules; appareils de locomotion par terre, par air ou par eau; parties de véhicules
Produits et services
T-shirts; Sweatshirts; Sleeved jackets; Sports caps and hats; Hats; Polo shirts; Sweaters Model planes; Toy models; Scale model kits Airplanes; Structural parts for airplanes
An aerospace wiring harness inspection system comprises a mobile personal computing device; a camera system connected to the mobile personal computing device, a machine learning model running in the mobile personal computing device; and a controller. The machine learning model is trained to detect anomalies in a set of images of a wiring harness in an aerospace vehicle. The controller configured to control the camera system to generate a set of images of the wiring harness; send the set of images of the wiring harness to the machine learning model; and receive a result from the machine learning model indicating whether an anomaly is present in the wiring harness.
A paper dispensing system and method include one or more housings defining an internal chamber configured to retain a roll of wound paper. The one or more housings includes internal surfaces, and an opening through which an edge of the wound paper is dispensable. An intumescent material is coupled to the one or more housings. The intumescent material is configured to expand to fill and close open areas including the opening within the one or more housings in response to being exposed to a predetermined temperature.
A47K 10/38 - Distributeurs de serviettes en papier ou de papier hygiénique distribuant à partir d'une bande continue, p. ex. avec des moyens de distribution mécaniques la bande continue étant enroulée
A62C 3/08 - Prévention, limitation ou extinction des incendies spécialement adaptées pour des objets ou des endroits particuliers dans les véhicules, p. ex. les véhicules routiers dans les avions
Systems, apparatus, articles of manufacture, and methods are disclosed for controlled material application. An example apparatus includes a pool to carry the application material, a thinning sheet, a roller mounted on an electronically controlled robot arm, machine readable instructions, and controller circuitry to at least one of execute or instantiate the machine readable instructions to direct the electronically controlled robot arm to maneuver the roller to contact the application material in the pool, at least partially submerge the roller in the application material, maneuver the roller to contact the thinning sheet to distribute the application material to surround the roller, and apply the application material to the component by moving the roller across at least a portion of the component.
B25J 9/04 - Manipulateurs à commande programmée caractérisés par le mouvement des bras, p. ex. du type à coordonnées cartésiennes par rotation d'au moins un bras en excluant le mouvement de la tête elle-même, p. ex. du type à coordonnées cylindriques ou polaires
An applicator that includes a body with a first end, an opposing second end, and an intermediate flange. An arm is connected to and extends radially outward from the body. During use, viscous material is positioned on the surface of the workpiece outward away from an opening. The first end of the applicator is inserted into the opening and a bottom side of the flange contacts against the surface of the workpiece. The arm is positioned relative to the flange to be above the surface of the workpiece with a gap formed between the bottom side of the arm and the workpiece. The applicator is rotated causing the arm to move around the opening and spread the viscous material across the surface of the workpiece.
B05C 11/02 - Appareils pour étaler ou répartir des liquides ou d'autres matériaux fluides déjà appliqués sur une surfaceRéglage de l'épaisseur du revêtement
B05C 21/00 - Accessoires ou instruments employés pour l'application des liquides ou d'autres matériaux fluides à des surfaces, non prévus dans les groupes
69.
System for Attaching Heat Generating Equipment to an Exterior of an Aircraft
A mounting system for attaching heat generating equipment to an exterior of an aircraft. The mounting system comprises an adapter plate connected to a fuselage of the aircraft; a layer of insulation substantially covering a first face of the adapter plate; a subplate formed of a conductive material and connected to the adapter plate such that the layer of insulation is positioned between the subplate and the adapter plate; heat generating equipment secured within the subplate; and a radome connected to the adapter plate and positioned to cover the heat generating equipment and the subplate.
B64C 1/36 - FuselagesCaractéristiques structurales communes aux fuselages, voilures, surfaces stabilisatrices ou organes apparentés adaptés pour recevoir des antennes ou des radômes
B64C 1/40 - Insonorisation ou isolation calorifique
A quantum computing device is provided, including a plurality of spin-based quantum-dot qubits that each include one or more quantum dots. The plurality of spin-based quantum-dot qubits also each include a nanomagnet including an amorphous ferromagnetic alloy.
Embodiments are shown for a machine and process to rotate and fix a second structure relative to a first structure via a hinge that may include a central axis, a lock-plate, and a moveable, a stationary, and a driving, member. The process may include: attaching a hinge to the first structure; moving a pin, extending parallel to the central axis through the stationary and driving members, out of a first notch of the movable member toward the central axis via rotating the driving member around the central axis; rotating the movable member via rotating the second structure around the central axis; fixing the movable member by latching the hinge via moving the pin away from the central axis and into a second notch in the movable member; and locking the latch by moving, along a length of the central axis, the lock-plate toward the driving member and the pin.
An end effector is presented. The end effector comprises a torque wrench and a first vacuum source. The torque wrench is configured to hold a collar and apply a single-sided clamp-up to a structure. The first vacuum source is pneumatically connected to the torque wrench and configured to supply a vacuum for the single-sided clamp-up.
Additive manufacturing systems are disclosed herein. The systems include a support platform, which is configured to support a manufactured component during additive manufacture of the manufactured component. The systems also include a feedstock supply system, which is configured to supply a feedstock material to an addition location on a previously formed portion of the manufactured component. The systems further include an energy source, which is configured to deliver an amount of energy to the addition location. The systems also include a controller.
Systems and methods for automated wire pickup using image-based robot guidance. The machine vision-based system includes: a robot arm; a tool head coupled to the distal end of the robot arm and including a wire gripper motor; a wire gripper movably coupled to the tool head and operatively coupled to the wire gripper motor; a wire holder configured for clamping a wire; camera means mounted to the distal end of the robot arm and having first and second fields of view which intersect in a volume of space that includes the tip of the wire gripper and the wire holder; and a computer system configured to control operation of the robot arm motors and wire gripper motor. More specifically, the computer system is configured for visually estimating the position and orientation of a contact-equipped wire being held by the wire holder and then generating robot guidance to enable automated pickup of the end section of the wire by the wire gripper.
A system and a method include a control unit configured to compare first QNH data received from a first QNH data source, second QNH data received from a second QNH data source that differs from the first QNH data source, and a QNH input entered into an avionics system of an aircraft. The control unit is further configured to output an alert signal in response to the QNH input differing from one or both of the first QNH data or the second QNH data.
A method includes implementing, via an electronic controller of an aircraft, an extend command received by the electronic controller from a flight control computer to rotate a wingtip of a wing to a flight position. The method includes, in response to a first determination at the electronic controller that rotation of the wingtip stopped before the flight position during implementation of the extend command, sending a first notification signal to the flight control computer from the electronic controller to cause the aircraft to be grounded and to schedule maintenance of the aircraft. The first notification signal includes one or more first error codes. The first notification signal causes the maintenance to include wingtip-to-latch pin drop maintenance responsive to a determination of the electronic controller indicating that a first particular angle of the wingtip relative to a primary portion of the wing is in a latch pin interference range.
A folding wingtip aircraft includes a wing that includes a primary portion and a wingtip. The folding wingtip aircraft includes a folding wingtip system configured to rotate the wingtip relative to the primary portion. The folding wingtip aircraft also includes a flight control computer. The flight control computer is configured to, in response to a first determination that a wingtip position of the wingtip is not in a folded position when a second determination indicates that a last completed command by the folding wingtip system was a fold command, set error codes for the folding wingtip system. The flight control computer is also configured to change a setting to indicate that the folding wingtip aircraft is grounded based on the error codes.
Methods and apparatus are disclosed for multilevel balancing of computational tasks, the multilevel balancing including interface circuitry to receive or access a batch of tasks; machine readable instructions; and programmable circuitry to at least one of instantiate or execute the machine readable instructions to allocate the batch of computational tasks into sets, distribute the sets to compute nodes, monitor the compute nodes for completion of the computational tasks, distribute ones of the computational tasks to computational resources of the respective compute nodes based on the monitoring of the completion of the computational tasks, monitor the compute nodes for completion of respective ones of the sets, distribute queued sets to the compute nodes based on the monitoring of the completion of the sets, and distribute queued tasks to the computational resources based on the monitoring of the completion of the tasks.
A system and method for attaching heat generating equipment to an exterior of an aircraft. The mounting system comprises a heat chamber formed by a number of conductive materials, the heat chamber having a recess open to an environment outside the aircraft, heat generating equipment secured within the recess, and a layer of insulation between the heat chamber and the aircraft, the layer of insulation positioned on an opposite side of the heat chamber than an opening of the recess.
The present disclosure provides a method of repairing a hat stringer. The method includes arranging a repair stringer in a mounting location that is one of a plurality of possible mounting locations along a cross section of a hat stringer. In each of the plurality of possible mounting locations, at least a portion of an internal profile of the repair stringer matches at least a portion of a profile of an internal cavity defined by the hat stringer. A cross-sectional area of the repair stringer as viewed along a first direction is less than a total cross-sectional area of the hat stringer as viewed along the first direction. The method also includes coupling the repair stringer with a stringer of the hat stringer in the mounting location. Repair stringers and repaired hat stringers are also provided.
A method for forming a composite part includes positioning a composite ply over a forming surface of a forming tool, moving a forming feature into engagement with the composite ply to yield a formed ply, and, after the moving, securing the formed ply relative to the forming tool.
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
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 70/54 - Parties constitutives, détails ou accessoiresOpérations auxiliaires
B29L 31/30 - Véhicules, p. ex. bateaux ou avions, ou éléments de leur carrosserie
82.
SYSTEMS AND METHODS FOR COORDINATING MAINTENANCE OF VEHICLES
A system and a method include a maintenance control unit configured to: receive a fault message regarding one or more components of an aircraft, determine a priority from the fault message, determine one or more parts for maintenance from the fault message, and determine a time and a location for the maintenance based on the priority and location of the one or more parts.
An electrical raceway installation apparatus and method for installing an electrical raceway into a floor grid assembly of an aircraft. The electrical raceway installation apparatus includes a backing for connection to the electrical raceway. Floor grid tooling includes a horizontal beam that supports a floor grid assembly of an aircraft. The horizontal beam has a cutout that provides space under the floor grid assembly for insertion of the backing and electrical raceway. A hoist is connected to the floor grid tooling and lifts the backing and the electrical raceway through the space to a position for attachment with the floor grid assembly of the aircraft.
Example implementations relate to systems and techniques for intuitive hot spot demarcation along ground surfaces in order to provide alerts that assist pilots avoid potential collisions. An aircraft computing system may receive map and hot spot data for a taxi route for the aircraft. Based on the map and hot spot data, the computing system may display a representation of the taxi route with a graphical overlay that conveys a position of each hot spot located along the taxi route. The computing system may monitor movement of traffic relative to the taxi route based on traffic data. When traffic is detected proximate a hot spot located along the taxi route, the computing system may provide an alert via the display interface. The alert can increase in intensity based on the location of the traffic relative to the hot spot.
A system includes a set of satellites in orbits having transits across the sky. Two or more such transits are arranged to intersect to form a closed loop. Movement of the satellites along their respective transits causes, at each intersection of the closed loop, two or more satellites of the set of satellites to be distanced from each other in a manner that enables coverage of the two or more satellites by a single beam of an antenna that tracks one of the satellites.
A fastener system for joining substrates of a workpiece with working and blind sides includes a nut member, a sleeve member and a bolt member. The nut member includes a nut bore with internal threads. The nut member is placed with the nut bore over a joining bore through the substrates on the blind side. The sleeve member includes an outer sleeve surface with a lubricious coating. The sleeve member is inserted in the joining bore from the working side. The bolt member includes a head portion, a threaded portion and a shank portion. The bolt member is inserted in a central bore of the sleeve member. The threaded portion engages with the internal threads of the nut member. As the bolt member becomes fully engaged, the shank portion causes radial expansion of the sleeve member, and the sleeve member provides an interference fit within the joining bore.
F16B 39/28 - Blocage des vis, boulons ou écrous dans lequel le verrouillage se fait en même temps que le vissage ou le serrage par organes particuliers portés par l'écrou ou le boulon ou par la forme particulière de ceux-ci
F16B 5/02 - Jonction de feuilles ou de plaques soit entre elles soit à des bandes ou barres parallèles à elles par organes de fixation utilisant un filetage
A method for parallel particle swarm optimization includes initializing multiple particle positions of multiple particles and multiple particle velocities of the particles in response to multiple design variables, where the particles represent multiple candidate designs within a solution space; parsing the particle positions and the particle velocities into multiple simulation input files in a current iteration of multiple iterations; and presenting the simulation input files in parallel to multiple simulation processors. The method includes simulating, with the simulation processors, the simulation input files in parallel to produce multiple simulation result files; computing multiple objective function values of the particles in response to the simulation result files; updating the particles in the solution space using particle swarm optimization based on the objective function values; and repeating the parsing, the presenting, the simulating, the computing, and the updating in each subsequent iteration of the iterations to identify a final design.
Methods and apparatus for verifying cabin and flight deck security are disclosed herein. An example apparatus includes interface circuitry, machine readable instructions, and programmable circuitry to at least one of instantiate or execute the machine readable instructions to receive output from an identifier, the identifier associated with a location of a passenger seat on an aircraft, receive output from a seat belt latch sensor, the seat belt latch sensor associated with a seat belt of the passenger seat, determine a usage status of the seat belt at the location of the passenger seat, and generate a seat diagram, the seat diagram including the usage status of the seat belt at the location of the passenger seat.
A system and methods for indexing an automated fiber placement head to a surface of a substrate are provided. The system comprises a first measurement system comprising a first plurality of sensors configured to scan the surface of the substrate; a second measurement system comprising a second plurality of sensors configured to locate the automated fiber placement head; and a data management device configured to generate a full resolution transformation using measurements from the first measurement system and determine a position of the automated fiber placement head using data from the second measurement system.
A device includes an antenna controller configured to direct a beam to track a first satellite that follows an orbit having a transit arranged to intersect a transit of one or more other satellites to form a closed loop. The antenna controller is also configured to switch a tracking target of the beam from the first satellite to a second satellite of the one or more other satellites when the first satellite and the second satellite are at a first intersection of the transits that form the closed loop.
A method of optimizing ground operations at an airport. The method includes receiving input information regarding the airport where the input information at least includes turnaround process information for aircraft at the airport. An allocation of ground resources and manpower is determined at the airport with a ground resource and manpower model based on the input information. The allocation of ground resources and manpower determined by the ground resource and manpower model with a machine learning model are iteratively optimized until an optimized allocation of ground recourse and manpower is generated that reduces idling of at least one of ground resources or manpower at the airport. A report is generated based on the optimized allocation of ground resources and manpower.
A fastener system for joining substrates of a workpiece with working and blind sides includes a binding barrel and a bolt. The binding barrel includes a cylindrical body with a proximal end, a distal end, a central bore and a flange. The central bore includes a counterbored portion and a threaded portion with internal threads. The binding barrel is inserted in a joining bore from the blind side. The barrel flange limits insertion of the binding barrel. The cylindrical body includes an outer surface with a lubricious coating. The bolt includes a head portion, a threaded portion and a shank portion. The bolt is inserted in the joining bore from the working side. The threaded portion engages with the binding barrel. As the bolt becomes fully engaged, the bolt causes radial expansion of the binding barrel, and the binding barrel provides an interference fit within the joining bore.
F16B 5/02 - Jonction de feuilles ou de plaques soit entre elles soit à des bandes ou barres parallèles à elles par organes de fixation utilisant un filetage
F16B 37/14 - Écrous-chapeauxChapeaux d'écrous ou de boulons
93.
METHODS AND APPARATUS TO REPAIR COMPOSITE AIRFOIL STRUCTURES
Systems, apparatus, articles of manufacture, and methods are disclosed to repair a semi-monocoque wing comprising: a doubler plate configured to be coupled to a skin of the semi-monocoque wing via a first adhesive, the doubler plate having a contour substantially complementary to a contour of a leading edge of the semi-monocoque wing; and a layer of tape positioned at least partially along at least a portion of an interface between an edge of the doubler plate and the leading edge of the skin.
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 73/10 - Réparation d'articles faits de matières plastiques ou de substances à l'état plastique, p. ex. d'objets façonnés ou fabriqués par utilisation de techniques couvertes par la présente sous-classe ou la sous-classe utilisant des éléments préformés utilisant des pastilles d'obturation appliquées à la surface de l'objet
94.
SYSTEMS AND METHODS FOR AUTONOMOUS VEHICLE PATH PLANNING
Systems and methods for autonomous vehicle path planning are described herein. An example vehicle includes an image sensor to obtain an image of a scene of an area surrounding the vehicle. The vehicle also includes navigation system circuitry to: analyze the image and generate a semantically segmented image that identifies one or more types of features in the image; project the semantically segmented image to a two-dimensional (2D) map projection; convert the 2D map projection into a cost map; and determine a path for the vehicle based on the cost map.
G05D 1/02 - Commande de la position ou du cap par référence à un système à deux dimensions
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
G06V 20/56 - Contexte ou environnement de l’image à l’extérieur d’un véhicule à partir de capteurs embarqués
A fastening system includes a first component and a second component. The fastening system includes a fastener assembly configured to attach together the first component and the second component. The fastening system also includes a layer disposed between the fastener assembly and the first component and/or the second component. The layer is configured to provide an alert when a predetermined compressive load has been reached in the first component and the second component which signals that a preload of the fastener assembly has been reached. A method of preloading a fastener assembly includes applying a torque to the fastener assembly until a predetermined compressive load has been reached in the first component and the second component. The alert of the layer is activated when the predetermined compressive load has been reached which signals that the preload of the fastener assembly has been reached.
F16B 31/02 - Assemblages à vis spécialement modifiés en vue de résister à une charge de tractionBoulons de rupture signalant ou limitant la charge de traction
98.
SURFACE PREPARATION FOR ELECTROLYTIC INORGANIC FINISHES
The present disclosure relates to substrate surface treatment methods and compositions. In at least one aspect, a method includes degreasing a metal substrate; performing a first alkaline cleaning on the metal substrate; etching the metal substrate by electropolishing techniques or with an alkaline etchant solution to form an etched metal substrate, wherein the etched metal substrate comprises an average surface roughness (Ra) of about 8 μin (0.2 μm) to about 16 μin (0.4 μm); deoxidizing the etched metal substrate to form a processed metal substrate; performing alkaline cleaning on the processed metal substrate; optionally performing etch-cleaning and deoxidizing if needed to remove oxides and depositing a coating onto the processed metal substrate to form a coated metal substrate.
Systems and methods for automatic magnetic variation detection include receiving, from a magnetic variation database, first magnetic variation data associated with an airport; determining second magnetic variation data based on a published approach associated with the airport and one or more trajectory measurements as an aircraft flies along a centerline of a localizer signal of the airport; determining a difference between the first magnetic variation data and the second magnetic variation data; and if the difference satisfies a deviation threshold, updating the magnetic variation database based at least on the second magnetic variation data.
Commonwealth Scientific and Industrial Research Organisation (USA)
Inventeur(s)
Hull, John
Zhang, Ning
Abrégé
An apparatus for determining alternating current (AC) losses in a superconductor sample is disclosed. The apparatus may comprise a sample holder configured to hold the superconductor sample and a frame configured to support the sample holder. The frame may include a pair of spaced apart parallel walls and may be configured to rotate about an axis of rotation. The apparatus may also comprise a rotor positioned between the pair of spaced apart parallel walls of the frame. The rotor may be configured to rotate about the axis of rotation to generate a magnetic field. Further, the apparatus may comprise an extension arm coupled to the frame and a sensor device configured to detect a force exerted on the sensor device by the extension arm.
G01N 27/72 - Recherche ou analyse des matériaux par l'emploi de moyens électriques, électrochimiques ou magnétiques en recherchant des variables magnétiques
G01N 1/42 - Traitement à basse température des échantillons, p. ex. cryofixation
