A method of using a fastener assembly includes aligning a first opening having a first diameter in a first component with a second opening having a second diameter in a second component and inserting a shaft having an outer diameter surrounded by a sleeve through the first opening and the second opening. The sleeve includes a proximal end, a distal end, an inner diameter, and an outer diameter. The method also includes compressing the proximal end and distal end of the sleeve to deform the sleeve and increase a wall thickness of the sleeve within at least one of the first opening or the second opening.
An aircraft maintenance user interface is provided. The interface comprises an alert indicator that displays an alert related to an aircraft system that must be addressed for maintenance compliance of an aircraft. A compliance window indicator displays a normalized sliding scale of elapsed percentage of a lead time between the alert and a maintenance compliance deadline. A remaining units indictor displays a number of used units out of a total number of allotted units that measure the remaining lead time.
B64F 5/60 - Test ou inspection des composants ou des systèmes d'aéronefs
G06Q 10/20 - Administration de la réparation ou de la maintenance des produits
G07C 5/00 - Enregistrement ou indication du fonctionnement de véhicules
G07C 5/08 - Enregistrement ou indication de données de marche autres que le temps de circulation, de fonctionnement, d'arrêt ou d'attente, avec ou sans enregistrement des temps de circulation, de fonctionnement, d'arrêt ou d'attente
A replacement stringer with angle members each having a flange and a web connected together along an elbow. The flange and web are positioned at an angle relative to each other. Slots extend inward from a lateral side of the web towards the elbow. The angle members are in an overlapping configuration along a length and a width of the replacement stringer with at least the webs of two or more of the angle members overlapping.
Example aircraft and aircraft evacuation slides and related methods are disclosed herein. An example evacuation slide assembly for an aircraft disclosed herein includes an inflatable slide body attachable to the aircraft and configured to inflate in response to an evacuation event, and a readiness indicator gate supported by the inflatable slide body, wherein the readiness indicator gate is movable from an unready position during inflation of the inflatable slide body, thereby indicating the inflatable slide body is not ready for use, to a ready position thereby indicating readiness of the inflatable slide body for user egress from the aircraft onto the inflatable slide body.
Disclosed herein is an applicator head and associated system and method for applying a coating to an object. The applicator head includes an elongated body with an external surface and an internal cavity. A coating inlet is formed in an upper portion of the elongated body and fluidically coupled with the internal cavity to enable a coating material to flow into the internal cavity from the coating inlet. A plurality of outlet ports are positioned along a lower portion of the elongated body and fluidically coupled with the internal cavity to enable the coating material to be dispensed from the internal cavity. A plurality of external ribs are disposed along the external surface of the elongated body and extend at a rib height from the external surface, at least one outlet port of the plurality of outlet ports is positioned between adjacent ones of the external ribs.
B05C 5/02 - Appareillages dans lesquels un liquide ou autre matériau fluide est projeté, versé ou répandu sur la surface de l'ouvrage à partir d'un dispositif de sortie en contact, ou presque en contact, avec l'ouvrage
B05C 11/06 - Appareils pour étaler ou répartir des liquides ou d'autres matériaux fluides déjà appliqués sur une surfaceRéglage de l'épaisseur du revêtement comportant un soufflage de gaz ou vapeur
B05C 17/00 - Outils à main ou appareils utilisant des outils tenus à la main pour appliquer ou étaler des liquides ou d'autres matériaux fluides sur des surfaces, pour enlever partiellement des liquides ou d'autres matériaux fluides des surfaces
6.
GENERALIZED ENTANGLEMENT FORGING WITH SLATER DETERMINANTS
Systems and techniques that facilitate generalized entanglement forging (GEF) of an electronic structure are provided. For example, one or more embodiments described herein can comprise a system, which can comprise a memory that can store computer executable components. The system can also comprise a processor, operably coupled to the memory that can execute at least one of the computer executable components that can generalize entanglement forging of an electronic structure for quantum operations, wherein GEF comprises initializing a calculation with a set of classical reference states, wherein the set of classical reference states are non-orthogonal Slater determinants. GEF can further comprise: correlating, on a quantum system, the set of classical reference states using a local unitary cluster Jastrow ansatz, wherein the Jastrow ansatz is initialized from a classical electronic structure calculation; and minimizing an energy function over a set of variational parameters of a wavefunction that represents the electronic structure.
An aircraft window barrier and aircraft window assembly including the aircraft window barrier for impeding debris entry into aircraft multi-pane windows during aircraft construction, aircraft storage, and non-flight aircraft phases, and methods for installing the aircraft window barrier and forming the aircraft window assembly are disclosed.
A blind fastener includes a sleeve defining a sleeve central axis and having a sleeve shank having a distal end portion and a proximal end portion axially opposed from the distal end portion and a stop connected to the distal end portion of the sleeve shank. The sleeve defines an eccentric through-bore that extends along a through-bore axis from the proximal end portion to the distal end portion. The blind fastener includes a core bolt at least partially received in the eccentric through-bore of the sleeve, defining a core bolt central axis. A core bolt shank has a distal end portion, a proximal end portion axially opposed from the distal end portion, and a threaded portion. A core bolt head is connected to the proximal end portion of the core bolt shank. An eccentric nut is threaded into engagement with the threaded portion of the core bolt shank.
A seal boot includes a base and a toe that extends from the base. The seal boot includes a fillet surface that is formed by the base and the toe. The seal boot includes a first fay surface that is at least partially formed by the base. The seal boot includes a second fay surface that is at least partially formed by the toe.
A module interface device for a multi-cell battery module comprises a cathode bus connectable to a cathode terminal and an anode bus connectable to an anode terminal of the battery module, and a set of one or more inter-cell taps connectable to respective inter-cell electrical interconnectors that interconnect neighboring pairs of cells of the battery module. The module interface devices comprises a cell balancing circuit that includes: an electrically conductive pathway that joins the cathode bus with the anode bus, a set of multiple resistive-capacitive elements arranged along the electrically conductive pathway, and a set of one or more switches in which a respective switch is located along each inter-cell tap. Each inter-cell tap joins the electrically conductive pathway at a respective location between a different neighboring pair of resistive-capacitive elements.
H01M 10/42 - Procédés ou dispositions pour assurer le fonctionnement ou l'entretien des éléments secondaires ou des demi-éléments secondaires
H01M 50/296 - MonturesBoîtiers secondaires ou cadresBâtis, modules ou blocsDispositifs de suspensionAmortisseursDispositifs de transport ou de manutentionSupports caractérisés par les bornes des blocs de batterie
H01M 50/298 - MonturesBoîtiers secondaires ou cadresBâtis, modules ou blocsDispositifs de suspensionAmortisseursDispositifs de transport ou de manutentionSupports caractérisés par le câblage des blocs de batterie
A captive fastener system and methods of installing captive fasteners are presented. A captive fastener system comprises an expandable opening with an initial diameter connected to a channel; and the channel. The channel has an internal diameter larger than the initial diameter and an exit diameter configured to retain a head of a fastener inside the channel.
A gauge for inspecting an aperture of a workpiece includes a body having a hole gauge portion configured to be disposed in a hole portion of the aperture and a countersink gauge portion configured to be disposed in a countersink portion of the aperture. The gauge includes a hinge connecting the hole gauge portion and the countersink gauge portion to allow the countersink gauge portion to move relative to the hole gauge portion. The gauge includes an indicator coupled to the body. The indicator is configured to indicate whether a predetermined tolerance is obtained between the countersink portion and the hole portion of the aperture. A method of determining a predetermined tolerance of an aperture of a workpiece uses the gauge.
G01B 3/52 - Calibres à tampon pour les dimensions intérieures avec des surfaces de contact dont l'écartement est fixe, mais peut être réglé à l'avance du type calibre à limitation, c.-à-d. calibre à tolérances maxima et minima réglables à l'avance en ce qui concerne l'usure ou les tolérances
13.
METHODS FOR MANUFACTURING COLD SPRAYED POWDER METALLURGY PREFORM
A method for manufacturing a cold sprayed powder metallurgy preform, the method including cold spraying a first metallic powder composition onto a substrate to yield a cold sprayed body and cold spraying a second metallic powder composition over the cold sprayed body to yield a cold sprayed canning layer on the cold sprayed body, wherein the cold sprayed canning layer includes a porosity of at most 3 percent.
B22F 7/04 - Fabrication de couches composites, de pièces ou d'objets à base de poudres métalliques, par frittage avec ou sans compactage de couches successives avec une ou plusieurs couches non réalisées à partir de poudre, p. ex. à partir de tôles
C23C 24/08 - Revêtement à partir de poudres inorganiques en utilisant la chaleur ou une pression et la chaleur
14.
SYSTEM AND METHOD FOR CORRELATING FORCES EXERTED BY DIFFERENT TOOLS
A system and a method include a component formed of a material. The component has one or more first holes. A test piece is formed of the material. The test piece has one or more second holes. A first tool is configured to insert one or more first fasteners into one or both of the first hole(s) or the second hole(s). A second tool is configured to insert one or more second fasteners into one or both of the first hole(s) or the second hole(s). One or more force sensors are coupled to one or both of the component or the test piece. The force sensor(s) are configured to detect (a) one or more first aspects of one or more first forces exerted during operation of the first tool to insert the first fastener(s) into one or both of the first hole(s) or the second hole(s), and (b) one or more second aspects of one or more second forces exerted during operation of the second tool to insert the second fastener(s) into one or both the first hole(s) or the second hole(s). A control unit is in communication with the force sensor(s), and is configured to correlate the first aspect(s) of the first force(s) with the second aspect(s) of the second force(s).
G01L 5/00 - Appareils ou procédés pour la mesure des forces, du travail, de la puissance mécanique ou du couple, spécialement adaptés à des fins spécifiques
A check valve is configured to be disposed within a fluid path. The check valve includes a housing, a poppet retained within the housing, and a state indication system operatively coupled to the poppet. The state indication system is configured to provide an indication of a first operational state of the check valve, and a second operational state of the check valve.
F16K 37/00 - Moyens particuliers portés par ou sur les soupapes ou autres dispositifs d'obturation pour repérer ou enregistrer leur fonctionnement ou pour permettre de donner l'alarme
F16K 15/06 - Soupapes, clapets ou valves de retenue à corps de soupapes rigides guidés par tige-guide
Manifolds and methods of connecting corrugated conduits are presented. A manifold to connect corrugated conduits is presented. The manifold comprises a first half, a second half removably connected to the first half to form a volume within the manifold, a first number of openings on a first end to access the volume, and a second number of openings on a second end to access the volume. Removing the first half from the second half cleaves each of the first number of openings and each of the second number of openings.
Disclosed herein is a method of preparing a bonding surface on a composite laminate and an associated composite laminate. The method involves forming a layup of multiple fiber-reinforced plies, including main body plies with a first combined thickness and peel plies with a second combined thickness. The method also includes selectively removing a portion of the main body plies along an edge to create an interim composite laminate with a lip defined by the peel plies. A force is applied to the lip to initiate a crack between the peel plies and the main body plies. The lip is then peeled away from the main body plies to remove the peel plies and expose a bonding surface on the composite laminate.
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
A device includes a memory and one or more processors coupled to the memory. The processor(s) are configured to obtain historical flight data that represents a plurality of flights associated with a plurality of airports and to generate a directed graph, based on the historical flight data, that includes a plurality of nodes and a plurality of edges connecting pairs of nodes. The plurality of nodes correspond to the plurality of airports and the plurality of edges correspond to the plurality of flights. The processor(s) are configured to perform a ranking operation on the directed graph to identify one or more target nodes of the plurality of nodes. The one or more target nodes correspond to one or more airports of the plurality of airports. The processor(s) are configured to output a graphical user interface that indicates the one or more airports as recommended airports for modeling predicted traffic flow.
A device includes a memory and one or more processors coupled to the memory. The one or more processors are configured to obtain statistics based on historical flight data for each of a plurality of historical flight paths. The historical flight paths are associated with historical flown distances between respective departure and arrival points. The one or more processors are configured to obtain an expected flown distance for an estimated flight path between a departure point and an arrival point. The one or more processors are configured to generate an airspace congestion metric associated with the estimated flight path. The airspace congestion metric is based on the expected flown distance and a set of the statistics associated with the departure and arrival points. The one or more processors are configured to output, based on the airspace congestion metric, a displayable airspace congestion indicator associated with the estimated flight path.
A reliability pattern classification system includes a communication device configured to obtain historical data indicative of usage of a component of a powered system, and a control unit that can create a visual representation of the historical data. The control unit also can identify one or more reliability patterns within the visual representation using a vision-based, deep learning model, categorize a failure mode of the component based on the one or more reliability patterns that are identified, and implement one or more responsive actions to change a state of condition of the component, the powered system, or both the component and the powered system.
A battery charging station is disclosed that includes an electrical system including a charging interface, a communications system including a wireless interface, and a control system. The control system is configured to receive a charging request to initiate a battery charging operation for a battery system of a mobile platform, establish a wireless communications link with the mobile platform via the wireless interface, and receive health status data for the battery system from the mobile platform over the wireless communications link via the wireless interface. The control system is further configured to enable charging of the battery system of the mobile platform via the charging interface responsive to the health status data satisfying a first condition, and to disable charging of the battery system of the mobile platform via the charging interface responsive to the health status data satisfying a second condition indicating a fault of the battery system.
Disclosed herein are a repair apparatus, system, and method for structurally reinforcing an abnormal composite structural member. The repair is suited for reinforcing a cured composite structure that defines a strength tolerance and has an abnormality that reduces the structural strength relative to the strength tolerance of the cured composite. The structural reinforcement repairs the abnormality in the cured composite and provides the repair strength so that the repaired composite has a structural strength that meets or exceeds the strength tolerance. The structural reinforcement has a composite patch that is coupled to the cured composite over the abnormality and is covered by pressure-sensitive tape.
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
B29L 31/30 - Véhicules, p. ex. bateaux ou avions, ou éléments de leur carrosserie
B32B 3/12 - Produits stratifiés comprenant une couche ayant des discontinuités ou des rugosités externes ou internes, ou une couche de forme non planeProduits stratifiés comprenant une couche ayant des particularités au niveau de sa forme caractérisés par une couche discontinue, c.-à-d. soit continue et percée de trous, soit réellement constituée d'éléments individuels caractérisés par une couche d'alvéoles disposées régulièrement, soit formant corps unique dans un tout, soit structurées individuellement ou par assemblage de bandes indépendantes, p. ex. structures en nids d'abeilles
B32B 5/02 - Produits stratifiés caractérisés par l'hétérogénéité ou la structure physique d'une des couches caractérisés par les caractéristiques de structure d'une couche comprenant des fibres ou des filaments
B32B 5/26 - Produits stratifiés caractérisés par l'hétérogénéité ou la structure physique d'une des couches caractérisés par la présence de plusieurs couches qui comportent des fibres, filaments, grains ou poudre, ou qui sont sous forme de mousse ou essentiellement poreuses une des couches étant fibreuse ou filamenteuse un autre couche également étant fibreuse ou filamenteuse
B32B 7/12 - Liaison entre couches utilisant des adhésifs interposés ou des matériaux interposés ayant des propriétés adhésives
B32B 15/14 - Produits stratifiés composés essentiellement de métal adjacent à une couche fibreuse ou filamenteuse
24.
SYSTEMS AND METHODS FOR LOCALLY CURING COMPOSITE STRUCTURES
A system for locally curing a composite structure includes a constraining container including a cover and having an interior volume. The cover is configured to enclose a portion of a composite structure. The system includes a retainer configured to hold the cover against the composite structure. The system included an expandable medium configured to be disposed within the interior volume of the cover between the walls and the composite structure.
A wing assembly includes an upper wing skin, a lower wing skin, and ribs extending between an upstream spar and a downstream spar with the upper wing skin and the lower wing skin at least partially enclosing the ribs. Each of the ribs includes a first rib portion having an upper wing skin engagement surface and a first rib engagement surface located on an opposite side of the first rib portion for the upper wing skin engagement surface and a second rib portion having a lower wing skin engagement surface and a second rib engagement surface. The second rib engagement surface on the second rib portion is secured to the first rib engagement surface on the first rib portion with rib fasteners.
A two-layer coating system for a composite component is presented. The two-layer coating system comprises a first layer configured to prevent transmission of at least one of ultraviolet light or visible light within desired wavelengths, and a second layer in contact with the first layer and configured to reflect infrared components of sunlight. The second layer comprises a polyurethane with titanium dioxide. The first layer is positioned between the second layer and the composite component.
Methods and apparatus for tail deployment in air launched effects (ALE) systems are disclosed. A disclosed example apparatus for deploying a tail for a launchable aircraft includes a spring having a first end and a second end, and a rotational hub operatively coupled to a rotational joint of a fuselage of the aircraft, the rotational hub operatively coupled to the first end of the spring, the second end of the spring operatively coupled to the tail, the spring to urge the tail to move relative to the fuselage when the aircraft is launched from a host.
Disclosed examples include accessing a listing of time values; accessing first compressed instrumentation data and second compressed instrumentation data during a runtime of an application in response to a request from the application; decompressing the first compressed instrumentation data during the runtime to generate first uncompressed instrumentation data in alignment with the time values; and decompressing the second compressed instrumentation data during the runtime to generate second uncompressed instrumentation data in alignment with the time values.
Boarding ladder systems for aircraft are disclosed herein. An example boarding ladder of an aircraft includes a linkage including a first support, a platform, and a second support, the linkage rotatable in a first plane, a lateral stop arm of the first support to engage a catch of the platform in a deployed position, engagement of the lateral stop arm and the catch to restrict rotation of the linkage in a first direction of rotation, and a post pivotally coupled to the platform, the post rotatable in a second plane with respect to the platform, the second plane different than the first plane, the post including a fastener enabling coupling of the post and the first support in the deployed position.
A method includes receiving a two-dimensional (2D) image from a camera, predicting 2D keypoints of a target object within the 2D image based on a previously trained ensemble of neural networks, and estimating 6 degree-of-freedom (6DOF) position (pose) of the target object using the 2D keypoints using a perspective-n-point (PnP) optimization technique to create 6DOF pose parameters for each neural network in the ensemble. The method combines the result into a single estimate of 6DOF pose parameters. The method also includes determining an uncertainty score based on a first uncertainty value and a second uncertainty value, and outputting the 6DOF pose parameters in response to the uncertainty score being within a predefined threshold.
A system and a method include a wheelchair, and a cart housing removably coupled to the wheelchair. The cart housing is configured to be selectively secured to and removed from the wheelchair. The system is operable as a galley cart when the cart housing is secured to the wheelchair. The system is operable as transfer chair when the cart housing is removed from the wheelchair.
Systems and methods for establishing a warmed potable water flow from an aircraft potable water supply with an ambient temperature absorbs and scavenges waste heat from an air chiller condenser exhaust of an air chiller circuit at a heat exchanger to pre-warm a potable water flow delivered to an aircraft galley appliance water heater, and to increase appliance water heating efficiency and to conserve electrical power for running aircraft galley appliance water heaters.
Systems and methods for establishing a warmed potable water flow from an aircraft potable water supply with an ambient temperature absorbs and scavenges waste heat at a heat exchanger to pre-warm a potable water flow delivered to an aircraft galley appliance water heater, and to increase appliance water heating efficiency and to conserve electrical power for aircraft galley appliance water heater operation are disclosed.
A system for driving a slat of an aircraft wing includes a primary support, an auxiliary support, an actuator support, and an actuator. The primary support is rotationally coupled to the slat at a forward slat revolute joint for moving the slat between a retracted position and one or more extended positions. The auxiliary support is coupled to the slat for pivoting the slat about the forward slat revolute joint when the slat moves between the retracted position and the one or more extended positions. The actuator support is coupled to the slat. The actuator is coupled to the actuator support at an aft slat revolute joint for driving the slat between the retracted position and the one or more extended positions.
Techniques for aerial vehicle tracking using dynamic aleatoric uncertainty covariance estimation are presented. The techniques include: obtaining an image depicting at least one aerial vehicle of interest; passing the image to a first machine learning subsystem, which provides at least one feature vector; inputting the at least one feature vector to a second machine learning subsystem, where the second machine learning subsystem is trained to provide detected aerial vehicle identification data sets (including respective aerial vehicle coordinates, respective aerial vehicle bounding box dimensions, and respective dynamic aleatoric uncertainty covariance values) corresponding to input feature vectors; providing at least one detected aerial vehicle identification data set to a recursive Bayesian estimator subsystem, from which at least one filtered set of aerial vehicle coordinates, representing a real-time location of a respective aerial vehicle of interest, is obtained; and outputting the at least one filtered set of aerial vehicle coordinates.
Techniques for localizing a vehicle in real time using dynamic uncertainty estimates are presented. The techniques include obtaining a terrain image captured by the vehicle; passing the terrain image to a trained evidential deep learning neural network subsystem, from which a dynamic uncertainty value and a first feature vector are obtained in real time; for each of a plurality of candidate terrain locations, comparing the first feature vector to a respective second feature vector representative of a candidate terrain location, from which a respective similarity score is obtained; for at least one of the plurality of candidate terrain locations, updating in real time, by a recursive Bayesian estimator, a respective location weight based on the dynamic uncertainty value and the respective similarity score; estimating, in real time, a location of the vehicle based on the plurality of location weights; and providing the location of the vehicle.
The present disclosure provides a method including: receiving flight sensor data and component fault data corresponding to a plurality of flights; applying a predictive model to individual flights of the plurality of flights to generate a plurality of fault probabilities for at least one aircraft component; selecting, based on a factor indicating a tolerance of false alerts, a plurality of settings comprising a minimum count of flights, a threshold probability, one or more detection window settings, and one or more alert group settings; detecting, based on the one or more detection window settings, a condition that at least the minimum count of flights within a detection window have a respective fault probability, of the plurality of fault probabilities, that is greater than the threshold probability; and determining, based on the one or more alert group settings, whether to generate a new alert for the condition.
The present disclosure provides techniques for efficient aircraft maintenance using a holographic automated manual display system. A voice query is received requesting maintenance information from one or more maintenance manuals. The voice query is processed to identify one or more keywords. A content management system (CMS) database is searched for the maintenance information based on the one or more keywords. The maintenance information is displayed via a holographic projection. A message is received that indicate an error in the maintenance information. In response to the interaction, the CMS database is updated to correct the error after validation within the maintenance information.
Disclosed herein are methods, systems, and aircraft for performing image analysis for aiding refueling operations. A method includes receiving a 2D image from a camera, determining a domain score for the 2D image based on previously defined training data, and sending the 2D image to the vision position estimation system in response to the domain score being greater than a predefined threshold, thus creating a sent 2D image.
A method for digital image display and interaction includes receiving an enhanced two-dimensional (2D) image comprising an image dataset derived from a digital object representation that includes spatial data representing a three-dimensional (3D) model of an object. A 2D display image included in the image dataset is displayed that depicts the object from a virtual camera location. User input is received associated with a selected pixel in the 2D display image having image-space coordinates within the enhanced 2D image. Based at least in part on the image-space coordinates of the selected pixel, a depth value for the selected pixel, a model view transformation matrix, and a projection matrix included in the image dataset, 3D object-space coordinates are calculated of a selected point on the object corresponding to the selected pixel. The 3D object-space coordinates of the selected point are displayed.
A surface inspection system for inspecting an inspection surface includes a three-dimensional (3D) scanner configured to scan the inspection surface and acquire a point cloud of points representing at least the localized portion. The localized portion includes a non-defective region and a suspect region at least partially surrounded by the non-defective region and potentially containing one or more defects. The surface inspection system includes a processor establishes a reference surface based on the points in the non-defective region and exclusive of the points in the suspect region, and the reference surface extends across the suspect region. The processor determine one or more characteristics of a shape of the point cloud relative to the reference surface within the suspect region.
A trajectory planning system for a refueling boom includes a human-machine interface (“HMI”) device and an electronic control unit (“ECU”). The HMI device outputs electronic control signals, in response to which the ECU performs a method. The ECU accesses a three-dimensional (“3D”) boundary model of the receiver and a 3D model of the boom. The ECU calculates a boom-to-receiver relative position using the models and sensor data, and a planned trajectory between a boom tip and a receptacle on the receiver. The trajectory is calculated using the boom-to-receiver relative position and predictive artificial potential fields. A point is found on a baseline trajectory farthest from a straight line between the receptacle and boom tip, which is recorded as a temporary goal. The planned trajectory avoids contact between the boom and receiver features. The ECU executes a control action using the planned trajectory.
A line management device for guiding local distribution of a utility line includes a main body with a middle portion, a first end portion and a second end portion. The middle portion includes a first end, a second end and a contoured surface extending between the first end and the second end. The contoured surface directs the utility line in relation to an object in a local environment. The first end portion abuts the first end of the middle portion and includes a first exterior surface shaped to direct the utility line toward the middle portion and to obstruct the utility line from passing over the first end portion. The second end portion abuts the second end of the middle portion and includes a second exterior surface shaped to direct the utility line toward the middle portion and to obstruct the utility line from passing over the second end portion.
H02G 3/04 - Tubes ou conduits de protection, p. ex. échelles à câbles ou goulottes de câblage
F16L 3/02 - Supports pour tuyaux, pour câbles ou pour conduits de protection, p. ex. potences, pattes de fixation, attaches, brides, colliers entourant partiellement le tuyau, le câble ou le conduit de protection
H02G 3/00 - Installations de câbles ou de lignes électriques ou de leurs tubes de protection dans ou sur des immeubles, des structures équivalentes ou des véhicules
44.
Device to Secure an Engine Cowling to an Aircraft Engine
A device to secure a cowl to an engine of an aircraft. The device has a support member with an elongated shape with a first end section configured to be connected to the engine and an opposing second end section configured to be connected to the cowl. A first connector and a second connector are positioned at the second end section to connect the support member to the cowl. The second connector is weaker than the first connector and configured to fail in a fan blade off event to enable the cowl to remain connected to the support member at the first connector and to enable the cowl to move radially outward away from the engine and the first end section of the support member.
A quantum entanglement system comprising a laser system, a spontaneous parametric down conversion crystal system, and a thermal management system. The laser system is configured to generate a laser beam. The spontaneous parametric down conversion crystal system comprises a spontaneous parametric down conversion crystal configured to receive the laser beam at a spontaneous parametric down conversion crystal and generate an entangled photon pair in response to the spontaneous parametric down conversion crystal receiving the laser beam. The thermal management system is configured to maintain the spontaneous parametric down conversion crystal at an annealing temperature during a generation of the entangled photon pair. A translation system is configured to move a position of the spontaneous parametric down conversion crystal. A
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
Systems and method of tracking cargo. The tracking system includes a wireless system with tags configured to be connected to the cargo and to emit identification data, and locators configured to be connected to the vehicle and receive the identification data emitted from the tags. A vision system includes cameras positioned in the vehicle and configured to capture images of the cargo. A control unit includes processing circuitry configured to identify the cargo and track a position of the cargo based on signals transmitted from the tags and received by the locators and track the position of the cargo based on the images captured by the vision system.
G06T 7/70 - Détermination de la position ou de l'orientation des objets ou des caméras
G06V 10/44 - Extraction de caractéristiques locales par analyse des parties du motif, p. ex. par détection d’arêtes, de contours, de boucles, d’angles, de barres ou d’intersectionsAnalyse de connectivité, p. ex. de composantes connectées
G06V 20/59 - Contexte ou environnement de l’image à l’intérieur d’un véhicule, p. ex. concernant l’occupation des sièges, l’état du conducteur ou les conditions de l’éclairage intérieur
H04W 4/029 - Services de gestion ou de suivi basés sur la localisation
H04W 4/80 - Services utilisant la communication de courte portée, p. ex. la communication en champ proche, l'identification par radiofréquence ou la communication à faible consommation d’énergie
Techniques for providing a display inside a vehicle are presented. The techniques can include: providing an electrophoretic surface integrated into an internal component of the vehicle, where the electrophoretic surface is flame resistant, and where the electrophoretic surface is configured to display an image within the vehicle; and controlling the electrophoretic surface using an electronic controller communicatively coupled to the electrophoretic surface.
B64D 11/00 - Arrangements pour passagers ou équipageInstallations de postes de pilotage non prévues ailleurs
G09G 3/34 - Dispositions ou circuits de commande présentant un intérêt uniquement pour l'affichage utilisant des moyens de visualisation autres que les tubes à rayons cathodiques pour la présentation d'un ensemble de plusieurs caractères, p. ex. d'une page, en composant l'ensemble par combinaison d'éléments individuels disposés en matrice en commandant la lumière provenant d'une source indépendante
H04N 7/18 - Systèmes de télévision en circuit fermé [CCTV], c.-à-d. systèmes dans lesquels le signal vidéo n'est pas diffusé
48.
SYSTEM AND METHOD FOR RESTRAINING A GALLEY CART WITHIN AN INTERNAL CABIN OF AN AIRCRAFT
A system and a method for restraining a galley cart within an internal cabin of a vehicle include a mounting frame configured to be secured to a wall within the internal cabin, and a cart restrainer moveably coupled to the mounting frame. The cart restrainer is configured to be moved between a stowed position against one or both of the wall or the mounting frame, and a deployed position that is configured to restrain the galley cart against one or both of the wall or the mounting frame.
The present disclosure provides a method of generating a balanced training dataset for a machine learning model in one aspect, the method including: receiving flight sensor data corresponding to a plurality of flights, and applying one or more criteria to the flight sensor data to generate a training dataset including a plurality of first instances corresponding to flights of the plurality of flights. The method further includes assigning, using component fault data, respective labels to the plurality of first instances, and generating, for groups of one or more labels of the respective labels, a respective plurality of flight series. Each flight series includes a respective sequence of second instances that is based on some of the plurality of first instances, and that concludes with a second instance that is assigned a label included in the group.
A monopole wideband antenna is provided. The monopole wideband antenna comprise a quartic monopole feed element connected to a center feed of a coaxial connector. A Vivaldi ground plane element is connected to a shield end of the coaxial connector, wherein the Vivaldi ground plane element comprises two vanes, each on opposite sides of the shield end of the coaxial connector. The quartic monopole feed element and Vivaldi ground plane element are in a common plane.
Disclosed herein is a modular pylon assembly for an aircraft. The pylon assembly includes a core module with an inboard side and an outboard side, each equipped with multiple sets of carriage-attachment elements. A forward post assembly and an aft post assembly extend from the core module and are removably mountable to the aircraft. The pylon assembly also includes a carriage module that can be removably attached to either the inboard side or the outboard side of the core module, using a selected set of carriage-attachment elements. Additionally, a suspension rack is mounted to the carriage module to support a payload. The core module is reconfiguration for left side or right side attachment to the aircraft.
A system for providing buoyancy for a vehicle on a body of water includes a support structure having an upper support end, a lower support end, and an interlocated portion between the upper and lower support ends, a first shell attached directly or indirectly to the support structure and having an upper first shell end and a lower first shell end, and a mechanism configured to move the first shell between a retracted state and a deployed state. In the retracted state, the upper first shell end is disposed proximate the interlocated portion and the lower first shell end is disposed proximate the lower support end, and in the deployed state, the first shell is disposed in one of a first arrangement, a second arrangement, a third arrangement and a fourth arrangement.
A system and method for achieving a high confidence threshold when asserting that the runway is clear of obstacles. A landing aircraft periodically scans runway regions to confirm, track, and propagate trajectories of self-reporting and non-cooperative objects. An incurring object, appearing as a very tiny artifact, is unlikely to be detected in every sensor frame. The system and method propagate the trajectories of the incurring objects to confirm that the objects will clear the runway before the aircraft lands by tracking the objects and using a probabilistic decision maker.
G01S 5/02 - Localisation par coordination de plusieurs déterminations de direction ou de ligne de positionLocalisation par coordination de plusieurs déterminations de distance utilisant les ondes radioélectriques
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
54.
TENSION LOAD FIXTURE AND METHOD FOR EVALUATING FRACTURE BEHAVIOR OF A COMPOSITE MATERIAL
A tension load fixture for applying tension or loading forces to a specimen comprises a pair of tension arms and an imaging device. The pair of tension arms are configured to releasably couple to opposite end regions of a specimen and to apply tension or loading forces to the specimen. The specimen is configured to be positioned between the pair of tension arms and defines a notch between the opposite end regions. The notch extends from a side of the specimen to a middle region of the specimen. The imaging device is configured to capture one or more images of the middle region and is configured to rotate about a central axis of the tension load fixture that is proximate to the middle region to facilitate generation of a three-dimensional image of the middle region as the specimen is subjected to tension or loading forces.
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
A rudder system of an aircraft includes a first shaft assembly and a second shaft assembly. Each of the first shaft assembly and the second shaft assembly includes a shaft, a trim crank coupled to the shaft, and a pedal crank. The trim crank is configured such that rotation of the trim crank causes rotation of the shaft, and pedal crank is configured such that rotation of the pedal crank causes rotation of the shaft without rotation of the trim crank. The rudder system includes a pedal input link configured to couple the pedal crank of the first shaft assembly and the pedal crank of the second shaft assembly together. The rudder system also includes a rudder trim link configured to couple the trim crank of the first shaft assembly and the trim crank of the second shaft assembly together.
The present disclosure provides a thermoelectric power system including one or more thermoelectric power devices for generating power. An example thermoelectric power device includes a thermoelectric generator, a first plate, and a second plate. A first side of the thermoelectric generator is at a higher temperature than a second, opposite, side of the thermoelectric generator. The first plate is disposed on the first side of the thermoelectric generator and includes a first surface coating that affects a heat absorption of the first plate. The second plate is disposed on the second side of the thermoelectric generator and includes a second surface coating that affects a heat absorption of the second plate.
H10N 10/17 - Dispositifs thermoélectriques comportant une jonction de matériaux différents, c.-à-d. dispositifs présentant l'effet Seebeck ou l'effet Peltier fonctionnant exclusivement par les effets Peltier ou Seebeck caractérisés par la structure ou la configuration de la cellule ou du thermocouple constituant le dispositif
B64D 27/32 - Aéronefs caractérisés par des groupes moteurs électriques à l'intérieur des fuselages ou fixés à ceux-ci
B64D 27/357 - Aménagements pour la production, la distribution, la récupération ou le stockage d'énergie électrique à bord utilisant des piles
57.
PITOT-STATIC INSTRUMENT TO DETERMINE AIRSPEED FOR AN AIRCRAFT
A pitot system includes a body including an inlet port and a hermetically sealed chamber positioned in the body. The hermetically sealed chamber includes a movable barrier in fluid communication with the inlet port. The pitot system also includes one or more first sensors configured to provide first signals, to a computer, based on deflection of the movable barrier due to impact pressure exerted against the movable barrier by fluid in the body. The first signals correspond to a stagnation pressure of fluid that entered the body via the inlet port.
A system and a method include a user interface including a display and an input device. The input device is configured to be operated to provide parameters for a flight of an aircraft. A control unit is in communication with the user interface. The control unit is configured to receive the parameters from the user interface, and determine one or both of emissions of the aircraft during phases of the flight of the aircraft, or emissions costs for the flight of the aircraft.
An aircraft system having a LIDAR system, one or more sensors, and a control unit. The control unit includes processing circuitry configured to calculate during flight a pressure altitude, calibrated airspeed, Mach number, equivalent airspeed, static temperature, static pressure, and dynamic pressure of an aircraft based on a combination of air data measurements from the LIDAR system and the one or more sensors.
Methods and apparatus for determinant assembly support are disclosed. A disclosed apparatus to orient, locate and support a panel component for assembly thereof includes a ball extending from an arm of a support frame for carrying the panel component, and a socket having a conical portion to receive the ball to couple the support frame to an assembly jig, the socket including a slot on at least one sidewall thereof to enable a clearance of the socket to the arm of the support frame.
Door latching systems, apparatus, articles of manufacture, and methods are disclosed. An example door latch includes a lever operatively coupled to a gear, the lever to rotate based on rotation of the gear, a worm screw operatively coupled to the gear, and a cam surface opposite the lever and fixed relative to the lever. The lever contacts the cam surface between a first rotational position and a second rotational position, the second rotational position different from the first rotational position.
An index tooling assembly for supporting a component during a manufacturing process includes a stationary support, a bracket fixed to the stationary support, and a locking assembly. A rail is fixed to the stationary support. The index tooling assembly includes an indexing assembly movably coupled to the rail to adjust a position of the indexing assembly. The indexing assembly includes at least one indexing feature configured to cooperate with a locating feature of the component. The locking assembly includes a post movably coupled to the bracket and a tongue supported via the post. The tongue is attachable to a clevis of the indexing assembly to move the indexing assembly linearly in response to movement of the post. The post is selectively locked in a final position to fix the indexing assembly in an initial position to prevent movement of the indexing assembly relative to the stationary support.
Methods and apparatus to manage transmissions between domains and memory are disclosed. An example electronic communications security system disclosed herein includes media storage; a first host bus adapter (HBA) serial attached small computer system interface (SCSI) (SAS) card to: communicatively couple a first domain to the media storage; and enable transmission of first data from the first domain to the media storage; and a second HBA SAS card that is write-block enabled to: communicatively couple a second domain to the media storage; enable access of the first data from the media storage by the second domain; and prevent second data from exiting the second domain.
Antenna elements include a metallic square ring patch and a metallic square ring slot to transmit or receive radio frequency (RF) signals. The antenna elements use several dielectric layers that are separated by a low-dielectric foam layer upon which the square ring patch is positioned. The antenna elements may be arranged into an antenna array that is tunable to collectively generate or receive RF signals to and from airborne and mobile vehicles with an agile, electronically scanning antenna array beam, with no moving parts. The antenna array includes a top section to communicate RF signals; a bottom section to generate a desired RF signal; and a foam layer between the top and bottom sections to separate the ring patch from the ring slot. High isolation between the top section and the bottom section allows the antenna elements to be used in higher gain and high-power arrays without adverse feedback issues.
A modular rail system for loading equipment through an aircraft entry door is provided. The rail system comprises a number of track adapters configured to attach to seat tracks in the floor of the aircraft and a number of detachable rail segments, wherein a subset of the rail segments is configured to attach to the track adapters at a prescribed angle relative to the seat tracks, wherein the angle is calculated to maximize clearance of equipment moved along the rail segments through the entry door based on the model of the aircraft.
A method for adhering a coating to a metal substrate is disclosed, which includes exposing a surface of a metal substrate to a solvent, applying a sol-gel treatment to the metal substrate, drying the treated metal substrate, applying a chemical reactivator to the treated metal substrate, and applying a polymer coating to the metal substrate. The method can include cleaning the metal substrate with an alkaline cleaner prior to exposing a surface of a metal substrate to a solvent. The polymer coating may include a polyurethane or a clear polymer coating. An article is disclosed, which includes a metal substrate, coated with a sol-gel coating layer, chemical reactivator layer, and a clear polymer coating.
B05D 7/14 - Procédés, autres que le flocage, spécialement adaptés pour appliquer des liquides ou d'autres matériaux fluides, à des surfaces particulières, ou pour appliquer des liquides ou d'autres matériaux fluides particuliers à du métal, p. ex. à des carrosseries de voiture
B05D 3/10 - Traitement préalable des surfaces sur lesquelles des liquides ou d'autres matériaux fluides doivent être appliquésTraitement ultérieur des revêtements appliqués, p. ex. traitement intermédiaire d'un revêtement déjà appliqué, pour préparer les applications ultérieures de liquides ou d'autres matériaux fluides par d'autres moyens chimiques
B05D 7/00 - Procédés, autres que le flocage, spécialement adaptés pour appliquer des liquides ou d'autres matériaux fluides, à des surfaces particulières, ou pour appliquer des liquides ou d'autres matériaux fluides particuliers
67.
METHODS FOR MANUFACTURING THERMALLY PROTECTED POLYMER COMPOSITE STRUCTURE
A method for manufacturing a thermally protected polymer composite structure using a thermal barrier layer, the thermal barrier layer being porous and including a tool-side surface and a non-tool-side surface opposed from the tool-side surface, the method including co-bonding an adhesive onto the non-tool-side surface of the thermal barrier layer to yield a coated thermal barrier layer comprising a coated surface, and co-bonding a polymer matrix composite material onto the coated surface of the coated thermal barrier layer.
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 7/12 - Liaison entre couches utilisant des adhésifs interposés ou des matériaux interposés ayant des propriétés adhésives
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
68.
THERMALLY PROTECTED POLYMER COMPOSITES AND ASSOCIATED METHODS
A polymer composite structure includes a polymer matrix composite material and a thermal barrier layer that is coupled to the polymer matrix composite material. The polymer composite structure is configured to resist a transient temperature spike in the polymer matrix composite material.
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
B64D 33/04 - Aménagement sur les aéronefs des éléments ou des auxiliaires des ensembles fonctionnels de propulsion, non prévu ailleurs des sorties d'échappement ou des tuyères
69.
ENVIRONMENTALLY PROTECTED POLYMER COMPOSITES AND ASSOCIATED METHODS
A polymer composite structure includes a polymer matrix composite material and an oxygen impermeable layer that is coupled to the polymer matrix composite material. The oxygen impermeable layer is configured to resist oxidation in the polymer matrix composite material.
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 25/20 - Produits stratifiés composés essentiellement de caoutchouc naturel ou synthétique comprenant du caoutchouc au silicone
B32B 27/28 - Produits stratifiés composés essentiellement de résine synthétique comprenant des copolymères de résines synthétiques non complètement couverts par les sous-groupes suivants
70.
Accumulator for Prevention of Hydraulic Pump Cavitation
To prevent cavitation damage to a hydraulic fluid pump, a low pressure accumulator is fluidly connected to the suction line of an engine-driven hydraulic pump to boost suction line pressures during instantaneous demands for higher pump flows. The accumulator acts as a localized reservoir for the engine-driven pump to avoid deleterious pressure drops which give rise to pump cavitation. In one disclosed architectural arrangement, the accumulator is directly coupled to the suction line of an aircraft engine-driven hydraulic pump to supply hydraulic fluid upon demand, with both the pump and accumulator contained within an engine nacelle of an aircraft. The low pressure accumulator operates fully independently of a remote main aircraft accumulator, and while the main accumulator operates at thousands of psi, and requires periodic service, the low pressure accumulator operates at less than 30 psi, and is formed of a maintenance-free construction.
A system and a method include a fall protection system having safety anchors coupled with a passenger basket of a lift system. Each of the safety anchors may receive a safety key. One or more sensors are operably coupled with the passenger basket or a base of the lift system. A controller including one or more processors receives data from the sensors. The controller determines a weight value based on the data that corresponds to one or more passengers disposed within the passenger basket. The controller determines a number of passengers that are disposed within the passenger basket based in part on the weight value. The controller controls one or more operations of the lift system based at least in part on a comparison between the number of passengers disposed within the passenger basket and a number of safety keys operably coupled with a corresponding safety anchor.
An apparatus associated with a vehicle, includes a body, wherein the body includes a chamber. The apparatus further includes a buoyancy ring coupled to the body. The apparatus further includes a battery located within the chamber. The apparatus further includes a transmitter, wherein a portion of the transmitter is disposed within a recess of the body. The apparatus further includes a processor located within the chamber and coupled to a memory device, wherein the processor is configured to: receive a signal indicating detection of submersion of the vehicle in water, send a signal to switch a power source from the vehicle to the battery, send a signal to cause inflation of an inflatable bag, and cause the transmitter to send a data transmission.
G07C 5/08 - Enregistrement ou indication de données de marche autres que le temps de circulation, de fonctionnement, d'arrêt ou d'attente, avec ou sans enregistrement des temps de circulation, de fonctionnement, d'arrêt ou d'attente
B64D 25/20 - Largage des indicateurs de position de détresse ou de chute
B64D 45/00 - Indicateurs ou dispositifs de protection d'aéronefs, non prévus ailleurs
B64F 5/60 - Test ou inspection des composants ou des systèmes d'aéronefs
G07C 5/00 - Enregistrement ou indication du fonctionnement de véhicules
73.
Display screen or portion thereof with animated graphical user interface
Bleed-air systems comprise a bleed-air turbine configured to receive at least a first portion of bleed air from a jet engine and deliver it to a cabin, a cabin-exhaust compressor operatively coupled to the bleed-air turbine and configured to receive cabin exhaust air from the cabin, and a cabin-exhaust nozzle configured to receive the cabin exhaust air from the cabin-exhaust compressor. Aircraft comprise a fuselage, a wing, a jet engine, and a bleed-air system. Methods comprise expanding at least a first portion of bleed air from a jet engine to drive a cabin-exhaust compressor, compressing cabin exhaust air from a cabin with the cabin-exhaust compressor, and nozzling the cabin exhaust air to environment.
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 13/02 - Aménagements ou adaptations des appareils de conditionnement d'air pour équipages d'aéronefs, passagers ou pour emplacements réservés au fret l'air étant pressurisé
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
F02C 9/18 - Commande du débit du fluide de travail par prélèvement, par bipasse ou par action sur des raccordements variables du fluide de travail entre des turbines ou des compresseurs ou entre leurs étages
75.
Transmission Systems to Selectively Transfer Power of a Turbine Engine
A transmission operatively connected to a turbine engine of an aircraft to selectively transfer power from a first pressure spool of the turbine engine to a second pressure spool of the turbine engine and to power an accessory. The transmission is configured to selectively operate in one of a first configuration and a second configuration. The first configuration transfers power from the turbine engine to the accessory and the second configuration transfers power from the first pressure spool to the second pressure spool.
A system configured to be operatively connected to a turbine engine of an aircraft and to an accessory of an aircraft. The system is configured to selectively transfer power between a first pressure spool of the turbine engine and a second pressure spool of the turbine engine and to power the accessory to deliver air to an aircraft system of the aircraft.
An object classification system may be present on a vehicle with a computing device connected to a sensor mounted on the vehicle. In response to an object positioned in a field of view of the sensor, the computing device may determine a state of the object after calculating a relative shape stability value for the object over time. The computing device may then deviate from a predetermined route for the vehicle in response to a classification of the object as a dynamic state.
B60W 60/00 - Systèmes d’aide à la conduite spécialement adaptés aux véhicules routiers autonomes
G01S 17/931 - Systèmes lidar, spécialement adaptés pour des applications spécifiques pour prévenir les collisions de véhicules terrestres
G05D 1/437 - Commande de la position ou du cap par référence à un système à deux dimensions pour les aéronefs lors de leur déplacement au sol
G06V 10/764 - Dispositions pour la reconnaissance ou la compréhension d’images ou de vidéos utilisant la reconnaissance de formes ou l’apprentissage automatique utilisant la classification, p. ex. des objets vidéo
An object classification system for a vehicle detects, with a computing device, a first field of view with a first sensor and a second field of view with a second sensor, each sensor mounted on the vehicle. The computing device may fuse the first field of view with the second field of view to form a unified detection report, which may be used to automate portions of a taxiing operation in response to information in the unified detection report.
G08G 5/06 - Systèmes de commande du trafic aérien pour la commande lorsque l'appareil est au sol
G06V 10/80 - Fusion, c.-à-d. combinaison des données de diverses sources au niveau du capteur, du prétraitement, de l’extraction des caractéristiques ou de la classification
G06V 20/56 - Contexte ou environnement de l’image à l’extérieur d’un véhicule à partir de capteurs embarqués
Methods and apparatus for wing deployment in air launched effects systems are disclosed. A disclosed apparatus for deploying a wing for an aircraft includes a rotational joint at a fuselage of the aircraft, a spring having a first end and a second end, and a hub defined by or operatively coupled to the wing, the hub operatively coupled to the first end of the spring, the second end of the spring operatively coupled to the fuselage, the spring to urge the wing to move relative to the fuselage when the aircraft is launched from a host.
B64C 3/56 - Repliage ou rabattement pour réduire l'encombrement de l'aéronef
B64F 5/10 - Fabrication ou assemblage d’aéronefs, p. ex. gabarits à cet effet
B64U 70/20 - Dispositions pour le lancement, le décollage ou l'atterrissage pour lancer ou capturer en vol les véhicules aériens sans pilote via un autre aéronef
B64U 101/00 - Véhicules aériens sans pilote spécialement adaptés à des utilisations ou à des applications spécifiques
80.
COMBINED AVIATION AND GROUND MAPPING FOR AIRCRAFT NAVIGATION
A computing system for combined aviation and ground mapping for aircraft navigation includes memory storing aviation map data, road map data, and instructions of an air-ground navigation program, and processing circuitry configured to implement the air-ground navigation program. The processing circuitry receives aircraft location data and destination data for a user of the aircraft. The destination data is cross-referenced with the road map data to validate a destination of the user, and a landing site proximate the destination is determined via the aviation map data. An air route segment from the location of the aircraft to the landing site and a ground route segment from the landing site to the destination are generated via respective algorithms. The air and ground route segments are combined to produce a combined air-ground navigation route, and a visual representation of the combined air-ground navigation route is output to a display device.
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
An extended diol composition is disclosed, including a first component including a diol oligomer and a second component including a bisdimethylamino silane species, where the first component is in molar excess to the second component, and where the diol oligomer has a number average molecular weight Mn of from about 500 g/mol to about 5,000 g/mol. The diol oligomer can be α,ω hydroxyl terminated, or further include an R group that is a polyether, such as a perfluoropolyether, polyoxymethylene, polyethylene glycol, polytetramethylene glycol, or poly(propane diol), or a polyester, such as poly(caprolactone), poly(lactic acid), or poly(glycolic acid). The bisdimethylamino silane species may include an R1 and R2 that can include CH3, vinyl, and phenyl. A method for making an extended diol composition is also disclosed.
C08G 18/50 - Polyéthers contenant des hétéro-atomes autres que l'oxygène
C08G 18/10 - Procédés mettant en œuvre un prépolymère impliquant la réaction d'isocyanates ou d'isothiocyanates avec des composés contenant des hydrogènes actifs, dans une première étape réactionnelle
C08G 18/38 - Composés de bas poids moléculaire contenant des hétéro-atomes autres que l'oxygène
82.
Composite PRN Code to Achieve Higher Effective Chip Rate for Lower Time-of-Arrival Error
Generating a composite pseudo random noise (PRN) code is provided. The method comprises receiving a wireless transmission having a noisy received original PRN code multiplexed with navigation data. A noiseless local replica original PRN code is generated within the receiver. A noiseless local replica compressed PRN code is then generated based on the noiseless local replica original PRN code. The noiseless local replica compressed PRN code has the same length as the noiseless local replica original PRN code and a higher chip rate. A sample-to-sample multiplication operation on the noisy received original PRN code and the noiseless local replica compressed PRN code generates a noisy received composite PRN code. The received wireless transmission is then tracked according to the noisy received composite PRN code.
A backscatter x-ray system has an x-ray device, a movable platform, and a processor. The x-ray device includes an x-ray emitter and an x-ray detector. The movable platform positions the x-ray device relative to a frontside of a structure. The processor is communicatively couplable to the x-ray device. The x-ray emitter emits x-rays that penetrate the structure from the frontside. The x-ray detector detects a backscatter of the x-rays reflected from the structure. The processor generates x-ray images of the structure based on the backscatter, and analyzes the x-ray images in a manner facilitating at least one of manufacturing and inspection of the structure.
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
84.
TEST FIXTURES AND METHODS FOR IMPROVING FIDELITY OF THERMAL OXIDATIVE STABILITY TESTING
A test fixture for improving fidelity of thermal oxidative stability testing includes an environmental test chamber and a test material holder. The environmental test chamber includes an enclosure and a controller. The enclosure with an opening that provides access to an internal compartment defining a chamber environment. The controller controls the chamber environment within the internal compartment. The test material holder, at least partially disposed in the internal compartment, holds a material under test. The environmental test chamber and the test material holder expose a frontside of the material under test to a first environment and expose a backside of the material under test to a different environment. Various test fixtures and methods for improving fidelity for thermal oxidative stability testing are provided.
An end effector and associated systems and methods for printing ink on a surface is disclosed. The end effector comprises a main block including a back plate. The end effector also includes a plurality of slice assemblies slidably coupled to the back plate. Each one of the plurality of slice assemblies includes a printhead and a y-actuator. The y-actuator is selectively operable to extend and retract the printhead, parallel to a y-axis in first directions, and relative to the back plate. The end effector further includes a plurality of z-actuators coupled to the back plate. Each one of the plurality of z-actuators is selectively operable to extend and retract a corresponding one of the plurality of slice assemblies, parallel to a z-axis in second directions, which is perpendicular to the y-axis and relative to the back plate.
B41J 25/00 - Mécanismes ou mouvements non prévus ailleurs
B05B 13/02 - Moyens pour supporter l'ouvrageDisposition ou assemblage des têtes de pulvérisationAdaptation ou disposition des moyens pour entraîner des pièces
B05B 13/04 - Moyens pour supporter l'ouvrageDisposition ou assemblage des têtes de pulvérisationAdaptation ou disposition des moyens pour entraîner des pièces les têtes de pulvérisation étant déplacées au cours de l'opération
B05B 15/68 - Aménagements de réglage en position des têtes de pulvérisation
B41J 3/407 - Machines à écrire ou mécanismes d'impression ou de marquage sélectif caractérisés par le but dans lequel ils sont construits pour le marquage sur des matériaux particuliers
B41J 25/304 - Mécanismes mobiles pour têtes d'impression ou chariots mobiles vers ou à partir de la surface du papier
B41J 29/38 - Entraînements, moteurs commandes ou dispositifs d'arrêt automatiques pour le mécanisme d'impression tout entier
The present disclosure provides methods of protecting a substrate from corrosion. The methods include applying a coating composition to a surface of the substrate. The coating composition includes a corrosion inhibitor including a metal organic framework (MOF). The metal organic framework includes a metal ion coordinated to one or more organic ligands. The one or more organic ligands include at least one exocyclic sulphur group. The metal ion of the MOFs includes a rare earth metal or transition metal. The coating composition includes a sealant including a non-stoichiometric sensitive composition and an activator.
Examples of the present disclosure include an apparatus that includes a syntactic-foam part. The syntactic-foam part includes low-density spheres at least partially embedded in a resin. The syntactic-foam part includes an elongated member partially embedded in the resin and including a first end and a second end. At least the first end is located relative to the syntactic-foam part such that the first end is exposed to an exterior of the syntactic-foam part at an exterior surface of the syntactic-foam part.
C08J 9/32 - Mise en œuvre de substances macromoléculaires pour produire des matériaux ou objets poreux ou alvéolairesLeur post-traitement à partir de compositions contenant des microbilles, p. ex. mousses syntactiques
92.
SYNTACTIC-FOAM PARTS AND ASSOCIATED METHODS OF MAKING THE SAME
Disclosed herein is a syntactic-foam part and associated methods for making the syntactic-foam part using a mold. The syntactic-foam part includes low-density spheres with at least one inner distribution media layer positioned within the low-density spheres at a predetermined height, that are encapsulated in a resin. The at least one inner distribution media layer facilitates resin flow along an entirety of the at least one distribution media layer before flowing out of the at least one inner distribution media layer, thus resetting a resin level at an infusion interface during an infusion process.
B29C 67/20 - Techniques de façonnage non couvertes par les groupes , ou pour la fabrication d'objets poreux ou cellulaires, p. ex. des mousses plastiques, des mousses alvéolaires
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
A method for pointing a laser beam. The laser beam is directed at a central location in a search area in which a satellite is expected to be located. The laser beam is moved in a path from the central location to an outer location. A number of scan parameters is adjusted during movement of the laser beam on the path.
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
94.
Nonuniform Laser Beam Scan Based Flight Path Clearing System
A method for clearing a flight path. A number of characteristics is selected for a laser beam based on an object type. The laser beam is emitted with the number of characteristics in a direction relative to a flight path of the aircraft. The laser beam with the number of characteristics selected for the object type is moved to scan an area using a path from a central location to an outer location of the area. A number of scan parameters is adjusted during scanning the area using the path. A number of objects of the object type hit by the laser beam is cleared from the flight path.
A sensor includes an emitter electrode configured to be disposed at a first position and exposed to a fluid airflow. The emitter electrode is configured to generate charged particles proximate the emitter electrode via a voltage pulse. The sensor includes a collector electrode configured to be disposed at a second position and exposed to the fluid airflow. The second position is aft of the first position. The collector electrode is configured to detect a current associated with a flow of the charged particles during relative movement of the fluid airflow. The sensor includes one or more processors coupled to the emitter electrode and the collector electrode, wherein the one or more processors are configured to measure a duration between the voltage pulse and the current, and wherein the duration is indicative of a speed of a vehicle.
G01P 5/00 - Mesure de la vitesse des fluides, p. ex. d'un courant atmosphériqueMesure de la vitesse de corps, p. ex. navires, aéronefs, par rapport à des fluides
B64D 43/02 - Aménagements ou adaptations des instruments pour indiquer la vitesse des aéronefs ou les conditions de décrochage
G01P 5/20 - Mesure de la vitesse des fluides, p. ex. d'un courant atmosphériqueMesure de la vitesse de corps, p. ex. navires, aéronefs, par rapport à des fluides en mesurant le temps mis par le fluide à parcourir une distance déterminée en utilisant des particules entraînées par un courant de fluide
96.
SYSTEM AND METHOD FOR MEASURING BIDIRECTIONAL REFLECTANCE DISTRIBUTION FUNCTION
A system for measuring a bidirectional reflectance distribution function (BRDF). The system includes a light source configured to generate light beams, a series of reflective elements and a two-axis mirror configured to direct the light beams. A beam splitter configured to allow allows a first portion of the light beams to pass therethrough. An ellipsoidal mirror is configured to receive the first portion of light beams at multiple predetermined locations on the ellipsoidal mirror as directed by the two-axis mirror with the two-axis mirror being located at a second focal point of the ellipsoidal mirror. The ellipsoidal mirror is configured to direct the first portion of light beams through a first focal point to reflect off a sample and generate reflected light beams. The reflected light beams are directed to the beam splitter and through a third focal point before being received by a first detector.
An adhesive formulation includes an epoxy-functional monomer or epoxy-functional polymer and an amino-phthalonitrile monomer or amino-phthalonitrile polymer. The adhesive formulation can include 4,4′-methylenebis(n,n-diglycidylaniline), bisphenol a diglycidyl ether, bisphenol f diglycidyl ether, n,n-diglycidyl-4-glycidyloxyaniline, 1,4-butanediol diglycidyl ether, trimethylolpropane triglycidyl ether, poly[(phenyl glycidyl ether)-co-dicyclo-pentadiene], or a combination thereof. The adhesive formulation may include a difunctional amine monomer, solvents, and one or more additives. A method of making an epoxy-phthalonitrile copolymer and a sandwich panel composition is disclosed. The sandwich panel can be a component of an aerospace structural application, such as a nacelle.
C09J 163/00 - Adhésifs à base de résines époxyAdhésifs à base de dérivés des résines époxy
B32B 3/12 - Produits stratifiés comprenant une couche ayant des discontinuités ou des rugosités externes ou internes, ou une couche de forme non planeProduits stratifiés comprenant une couche ayant des particularités au niveau de sa forme caractérisés par une couche discontinue, c.-à-d. soit continue et percée de trous, soit réellement constituée d'éléments individuels caractérisés par une couche d'alvéoles disposées régulièrement, soit formant corps unique dans un tout, soit structurées individuellement ou par assemblage de bandes indépendantes, p. ex. structures en nids d'abeilles
B32B 7/12 - Liaison entre couches utilisant des adhésifs interposés ou des matériaux interposés ayant des propriétés adhésives
B32B 15/04 - Produits stratifiés composés essentiellement de métal comprenant un métal comme seul composant ou comme composant principal d'une couche adjacente à une autre couche d'une substance spécifique
B32B 15/08 - Produits stratifiés composés essentiellement de métal comprenant un métal comme seul composant ou comme composant principal d'une couche adjacente à une autre couche d'une substance spécifique de résine synthétique
B32B 15/18 - Produits stratifiés composés essentiellement de métal comportant du fer ou de l'acier
B32B 15/20 - Produits stratifiés composés essentiellement de métal comportant de l'aluminium ou du cuivre
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
The present disclosure provides techniques for improving aircraft machining process using machine learning-based predictive models and many-objective optimization algorithms. Data from a machining process is collected, where the data comprises a plurality of machining parameters and at least two performance metrics. For each respective performance metric, a respective predictive model is trained using one or more machine learning (ML) techniques, where the plurality of machining parameters are used as inputs, the respective performance metric as target outputs, and the respective predictive model learns to correlate the inputs to the target output. For each respective performance metric, a respective objective function is generated for the respective predictive model. Many-objective optimization is performed on the respective objective functions, and a set of solutions are generated for the machining process based on the many-objective optimization.
An aircraft apparatus comprises a flight control surface, an actuation assembly, a link, and an arm. The actuation assembly transitions the flight control surface between a stowed configuration and a deployed configuration. The link is pivotably coupled to a support and comprises a stop surface. The arm is connected to the flight control surface and is pivotally coupled to the link. The arm comprises a contact surface arranged to engage the stop surface to limit pivotal movement of the arm relative to the link and thus define the deployed configuration of the flight control surface.
An aircraft apparatus comprises a flight control surface, an actuation assembly, a link, and an arm. The actuation assembly transitions the flight control surface between a stowed configuration and a deployed configuration. The link is pivotably coupled to a support and comprises a stop surface. The arm is connected to the flight control surface and is pivotally coupled to the link. The arm comprises a contact surface arranged to engage the stop surface to limit pivotal movement of the arm relative to the link and thus define the deployed configuration of the flight control surface.
A method comprises translating an arm and a flight control surface in a first direction towards a deployed configuration while simultaneously rotating a link. The method further comprises bringing the arm and the stop surface of link into contact to stop translation of the arm at the deployed configuration of the flight control surface.
Techniques for sending data over a computer network from an origination computer to a destination computer are presented. The techniques include: receiving a demand communication from the origination computer, where the demand communication specifies at least one network parameter; determining that a path through the network from the origination computer to the destination computer that complies with the at least one network parameter is not available; sending data from the origination computer to a node in the network over a path that complies with the at least one network parameter, where the node is not the destination computer; and storing the data at the node in persistent memory.
