A tail-rotor vibration dampener system for an aircraft is provided. The system includes a fuselage and an open rotor assembly including a powerplant and a set of rotor blades. The system further includes at least one actuator unit connecting the open rotor assembly to the fuselage. The actuator unit includes a hydraulic actuator controlling a position of the open rotor assembly in relation to the fuselage and a dampening device operable to cancel a vibration emanating from the open rotor assembly. The system further includes a computerized vibration dampening controller, including programming to determine a frequency of the vibration emanating from the open rotor assembly and control the dampening device to cancel the vibration emanating from the open rotor assembly based upon the frequency.
A transfer assembly to transfer power within an aircraft. The transfer assembly includes a low pressure drive mechanism operatively connected to a low pressure spool, a high pressure drive mechanism operatively connected to the high pressure spool, an accessory drive mechanism operatively connected to the accessory, and a differential operatively connected to each of the low pressure drive mechanism, the high pressure drive mechanism, and the accessory drive mechanism. The differential is configured to operate in a first mode configured to transfer power from the accessory to one of the low pressure spool and the high pressure spool, a second mode configured to transfer power from one of the low pressure spool and the high pressure spool to the accessory, and a third mode configured to transfer power from the low pressure spool to the high pressure spool.
F02C 7/32 - Aménagement, montage ou entraînement des auxiliaires
F02C 7/36 - Transmission de puissance entre les différents arbres de l'ensemble fonctionnel de turbine à gaz, ou entre ce dernier et l'utilisateur de puissance
3.
DEEP REINFORCEMENT LEARNING FOR AIRPLANE COMPONENT FAILURE PROGNOSTIC FULL CYCLE AUTOMATION
The present disclosure provides techniques for deep reinforcement learning to achieve full-cycle automation in airplane component failure prognostics. Flight data is preprocessed to identify parameters representing operational characteristics of an airplane component. A reinforcement learning framework is formulated based on the preprocessed flight, comprising defining a state representation as an input to a policy model, determining an action of sending an alert or not based on the state representation, modeling one or more system behaviors in response to the action using the preprocessed flight data, calculating a reward of the action under the state representation using a predefined reward structure, collecting training data by simulating an airplane component prognostic procedure. The policy model is trained using a learning and optimization algorithm with the training data to increase an expected discounted cumulative reward by choosing an action under the state representation.
A projector includes a housing, a display controller, a display engine, and a drive assembly. The display controller is coupled to the housing. The display engine is enclosed in the housing and is coupled to the display controller. The drive assembly is coupled to the housing and is configured to selectively position the housing.
Four-bar flapping rotors for aircraft and associated methods are disclosed. An example a flapping rotor hub described herein includes a rotor hub having a first end and a second end, the first end opposite the second end along an axis of rotation of the rotor hub, a first link rotatably coupled to the rotor hub at the first end, the first link to rotate in a plane parallel to the axis of rotation, a second link rotatably coupled to the rotor hub at the second end, the second link to rotate in the plane, and a pitch housing rotatably coupled to the first link at a third end of the pitch housing, the pitch housing rotatably coupled to the second link at a fourth end of the pitch housing, the pitch housing to rotate and translate in the plane, the pitch housing to receive a rotor blade.
A method for protecting an underlying structure from directed energy including combining an intumescent material with the underlying structure. The intumescent material forms a barrier to directed energy received on the intumescent material, the barrier suppressing or impeding transmission of the directed energy, and heat generated in the barrier by the directed energy, to the underlying structure.
B05D 5/00 - Procédés pour appliquer des liquides ou d'autres matériaux fluides aux surfaces pour obtenir des effets, finis ou des structures de surface particuliers
B05D 3/06 - 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 exposition à des rayonnements
G01N 17/00 - Recherche de la résistance des matériaux aux intempéries, à la corrosion ou à la lumière
7.
ROBOTIC LASER ABLATION SYSTEM WITH PROGRAMMATIC SURFACE-FIT MOTION PATH GENERATION
Described herein is a robotic laser ablation system that comprises a robot and processing circuitry. The robot has an end effector with laser componentry and a camera mounted thereto. Processing circuitry is configured, in response to stored instructions, to perform operations including: receiving the input image of a workpiece from the camera; segmenting the input image to produce an image segment that depicts at least a portion of the workpiece; applying a surface-fitting algorithm to generate a polynomial surface that is fit to the surface in the image segment; computing a set of surface normal vectors across the polynomial surface to generate a set of waypoints offset from the polynomial surface by an offset length; programmatically generating a motion path linking a plurality of the waypoints; and performing laser ablation of the surface of the portion of the workpiece based on the motion path.
Systems and methods of depositing a nanostructure including a compound, or salt thereof. The compound includes a plurality of N-alkylacrylamide units. The compound includes a moiety represented by the formula (I), wherein R1 is C1-C20 alkyl. The compound includes a moiety represented by the formula (II), wherein R2, R3, and R4 are each independently hydrogen or C1-C20 alkyl. The compound includes a plurality of moieties represented by the formula (III): R5 wherein R5 is C4-C10 aryl. The compound includes a plurality of moieties represented by the formula (IV), wherein Q is O or N, R** is C1-C20 alkyl, R6, R7, and R8 are independently C1-C6 alkyl or hydrogen and R9, if present, is C1-C16 alkyl, C1-C6 alkylyne, azole, guanidine, an oligomer of guanidine such as diguanidine, polysaccharide, chromophore, and combination(s) thereof, q is an integer of 0 or 1. In at least one instance of the plurality, R9 is present and is diguanidine.
Systems and methods of depositing a nanostructure including a compound, or salt thereof. The compound includes a plurality of N-alkylacrylamide units. The compound includes a moiety represented by the formula (I), wherein R1 is C1-C20 alkyl. The compound includes a moiety represented by the formula (II), wherein R2, R3, and R4 are each independently hydrogen or C1-C20 alkyl. The compound includes a plurality of moieties represented by the formula (III): R5 wherein R5 is C4-C10 aryl. The compound includes a plurality of moieties represented by the formula (IV), wherein Q is O or N, R** is C1-C20 alkyl, R6, R7, and R8 are independently C1-C6 alkyl or hydrogen and R9, if present, is C1-C16 alkyl, C1-C6 alkylyne, azole, guanidine, an oligomer of guanidine such as diguanidine, polysaccharide, chromophore, and combination(s) thereof, q is an integer of 0 or 1. In at least one instance of the plurality, R9 is present and is diguanidine.
A method for forming composite parts includes loading an uncured composite material into a middle cavity of a chamber between an upper membrane and a lower membrane, wherein a lower cavity is defined below the lower membrane, and wherein an upper cavity is defined above the upper membrane, wherein a forming tool is disposed within the upper cavity. A vacuum is applied to the upper cavity, the middle cavity, and the lower cavity to remove at least a portion of gas entrapped within the uncured composite material. The vacuum is released from the upper cavity and the lower cavity, and the chamber is heated to a forming temperature of the uncured composite material. Pressure is controlled in the upper cavity and the lower cavity to form the heated composite material, wherein a greater pressure is applied to the lower cavity than to the upper cavity such that a pressure differential between the lower cavity and the upper cavity causes the heated composite material to form around the forming tool. The chamber is heated to a curing temperature to cure the heated composite material.
B29C 70/44 - Façonnage ou imprégnation par compression pour la fabrication d'objets de longueur définie, c.-à-d. d'objets distincts utilisant une pression isostatique, p. ex. moulage par différence de pression, avec un sac à vide, dans un autoclave ou avec un caoutchouc expansible
B29C 70/54 - Parties constitutives, détails ou accessoiresOpérations auxiliaires
B29K 105/08 - Présentation, forme ou état de la matière moulée contenant des agents de renforcement, charges ou inserts de grande longueur, p. ex. ficelles, mèches, mats, tissus ou fils
11.
SYSTEM AND METHOD FOR MEASURING A BULB DIAMETER OF AN INSTALLED ONE-SIDED FASTENER IN A STRUCTURE
There is provided a computer-implemented system for measuring a bulb diameter of an installed one-sided fastener in a structure. The system includes the structure and the installed one-sided fastener installed in the structure. The installed one-sided fastener has a fastener bulb with the bulb diameter. The system includes an optical imaging system. The system includes image data, including a first image of the fastener bulb, and a second image of the fastener bulb. The system includes a post image processing system, to process the image data, and to determine a bulb diameter measurement of the bulb diameter. The post image processing system includes a control system with a computer system, a trained artificial intelligence model trained to identify the installed one-sided fastener and to define edges of the installed one-sided fastener, and one or more of, an edge detection process, an ellipse fitting process, and a stereo vision process.
G01B 11/10 - Dispositions pour la mesure caractérisées par l'utilisation de techniques optiques pour mesurer des diamètres d'objets en mouvement
B64F 5/60 - Test ou inspection des composants ou des systèmes d'aéronefs
G06V 10/82 - Dispositions pour la reconnaissance ou la compréhension d’images ou de vidéos utilisant la reconnaissance de formes ou l’apprentissage automatique utilisant les réseaux neuronaux
A method for testing a feed antenna of a satellite includes generating a source signal internal to the satellite. The satellite includes the feed antenna disposed on an exterior of the satellite. A transmit signal external to the satellite is generated by a broadcast of the source signal with the feed antenna. A test signal with a probe is generated in response to a first reception of a test portion of the transmit signal. The probe is external to the satellite. A reference signal with a reference horn is generated in response to a second reception of a reference portion of the transmit signal. The reference horn is external to the satellite. An amplitude and a phase of the transmit signal are determined based on the test signal relative to the reference signal.
Apparatus and methods for transonic truss-braced wing aircraft are disclosed herein. An example aircraft disclosed herein includes a fuselage and a wing supported by a truss. The truss includes a pylon coupled to and extending from the fuselage and a strut attached to the wing. An engine is coupled to the pylon.
The present disclosure provides a brace having a first leg and a second leg offset from the first leg. The brace also has a pivot assembly having a bar pivotably coupled with the first leg to define a first pivot point and pivotably coupled with the second leg to define a second pivot point. The brace further includes first and second attachment assemblies coupled with the first leg and the second leg, respectively, and each arranged to couple to a portion of a structure. In addition, the brace includes an actuator assembly coupling the first leg with the second leg and having an actuator arranged to pivot, or maintain a position of, the first leg relative to the first pivot point and to pivot, or maintain the position of, the second leg relative to the second pivot point so as to control a load on, and deflection of, the structure.
A method and apparatus for fastening two parts together. An initial interference fit may be created between a fastener and at least a portion of a hole extending through the two parts while maintaining a force equilibrium. A final interference fit may be created between the fastener and the hole, while maintaining a new force equilibrium.
B29C 39/02 - Moulage par coulée, c.-à-d. en introduisant la matière à mouler dans un moule ou entre des surfaces enveloppantes sans pression significative de moulageAppareils à cet effet pour la fabrication d'objets de longueur définie, c.-à-d. d'objets séparés
B29C 39/10 - Moulage par coulée, c.-à-d. en introduisant la matière à mouler dans un moule ou entre des surfaces enveloppantes sans pression significative de moulageAppareils à cet effet pour la fabrication d'objets de longueur définie, c.-à-d. d'objets séparés en incorporant des parties ou des couches préformées, p. ex. coulée autour d'inserts ou sur des objets à recouvrir
B29C 39/12 - Fabrication d'objets multicouches ou polychromes
B29C 39/22 - Éléments constitutifs, détails ou accessoiresOpérations auxiliaires
B29C 45/14 - Moulage par injection, c.-à-d. en forçant un volume déterminé de matière à mouler par une buse d'injection dans un moule ferméAppareils à cet effet en incorporant des parties ou des couches préformées, p. ex. moulage par injection autour d'inserts ou sur des objets à recouvrir
B29C 65/70 - Assemblage d'éléments préformésAppareils à cet effet par moulage
B60G 3/14 - Suspensions élastiques pour une seule roue avec un seul bras articulé le bras étant sensiblement parallèle à l'axe longitudinal du véhicule le bras étant rigide
B60G 7/00 - Bras de suspension articulésLeurs accessoires
B64C 1/00 - FuselagesCaractéristiques structurales communes aux fuselages, voilures, surfaces stabilisatrices ou organes apparentés
G05B 19/418 - Commande totale d'usine, c.-à-d. commande centralisée de plusieurs machines, p. ex. commande numérique directe ou distribuée [DNC], systèmes d'ateliers flexibles [FMS], systèmes de fabrication intégrés [IMS], productique [CIM]
G05D 1/00 - Commande de la position, du cap, de l'altitude ou de l'attitude des véhicules terrestres, aquatiques, aériens ou spatiaux, p. ex. utilisant des pilotes automatiques
G05D 3/12 - Commande de la position ou de la direction utilisant la contre-réaction
B23P 21/00 - Machines pour l'assemblage de nombreuses pièces différentes destinées à composer des ensembles, avec ou sans usinage de ces pièces avant ou après leur assemblage, p. ex. à commande programmée
B60P 3/025 - Véhicules adaptés pour transporter, porter ou comporter des charges ou des objets spéciaux l'objet étant une boutique, une cafétéria ou un étalage
16.
SYSTEM ARCHITECTURE FOR SECURE HIGHLY AVAILABLE MICROSERVICE APPLICATIONS WITH DECENTRALIZED AUTHORIZATION USING SHORT-LIVED TOKENS FOR SECURITY ENFORCEMENT IN CLOUD PLATFORMS
A device includes one or more processors configured to receive an authentication request indicating credentials of a requestor. The one or more processors are also configured to determine, based on the credentials, whether the requestor is authorized. The one or more processors are further configured to, responsive to determining that the requestor is authorized, generate a first authentication token. The one or more processors are also configured to, responsive to determining that the first authentication token has expired, determine whether the requestor remains authorized based on the credentials. The one or more processors are further configured to, responsive to determining that the requestor remains authorized, generate a second authentication token.
H04L 9/32 - Dispositions pour les communications secrètes ou protégéesProtocoles réseaux de sécurité comprenant des moyens pour vérifier l'identité ou l'autorisation d'un utilisateur du système
A mount to connect a fan cowl support beam to an engine fan case of an aircraft. The mount has a primary load path component and a secondary load path component. The primary load path component is configured to fuse upon application of a force from the fan case that is above a predetermined threshold. The secondary load path component is configured to remain functional upon application of the force above the predetermined threshold to maintain the fan cowl support beam connected to the fan case.
A mount to connect a fan cowl support beam to a fan case. The mount comprises a connector with spacers. The spacers have slots that are positioned between a first end and a second end. The spacers are configured to buckle upon application of a force from the fan case that is above a predetermined amount to absorb a portion of the force.
Disclosed examples include a first surface; a second surface opposing the first surface; a perimetric barrier along a perimeter of the second surface, the perimetric barrier protruding away from the second surface; an aperture formed through the first and second surfaces; and structural features formed on the second surface, the structural features extending between the aperture and the perimetric barrier.
G01N 29/44 - Traitement du signal de réponse détecté
G01N 29/22 - Recherche ou analyse des matériaux par l'emploi d'ondes ultrasonores, sonores ou infrasonoresVisualisation de l'intérieur d'objets par transmission d'ondes ultrasonores ou sonores à travers l'objet Détails
20.
PNEUMATIC VALVES, PNEUMATIC APPARATUSES, AND METHODS FOR CONTROLLING PNEUMATIC FLOW
A pneumatic valve includes a valve body, a valve chamber, an inlet port, a tool port, an accessory port, and a valve plug. The valve chamber has a longitudinal axis. The inlet port is formed through the valve body non-parallel to the longitudinal axis. The tool port is formed through the valve body non-parallel to the longitudinal axis. The accessory port is formed through the valve body parallel to the longitudinal axis. The valve plug is situated in the valve chamber and is movable along the longitudinal axis to selectively open and close a pneumatic flow between the inlet port, the accessory port, and the tool port in response to relative pressure differential between the valve chamber and the inlet port.
F16K 3/24 - Robinets-vannes ou tiroirs, c.-à-d. dispositifs obturateurs dont l'élément de fermeture glisse le long d'un siège pour l'ouverture ou la fermeture à faces d'obturation en forme de surfaces de solides de révolution avec corps de tiroir cylindrique
B23Q 5/06 - Entraînement des principaux organes de travail des arbres rotatifs, p. ex. des broches de travail entraînés principalement par des moyens hydrauliques ou pneumatiques
F16K 31/12 - Moyens de fonctionnementDispositifs de retour à la position de repos actionnés par un fluide
A system and a method include a lower support, an upper support, a first coupler connected to the lower support and the upper support at a first point of contact and a second point of contact, respectively, and a second coupler connected to the lower support and the upper support at a third point of contact and a fourth point of contact, respectively. The first coupler and the second coupler are configured to retain a test article therebetween.
G01N 3/20 - Recherche des propriétés mécaniques des matériaux solides par application d'une contrainte mécanique en appliquant des efforts permanents de flexion
G01N 3/06 - Adaptations particulières des moyens d'indication ou d'enregistrement
22.
Display screen or portion thereof with animated graphical user interface
Insulating ceramic panels and methods of forming insulating ceramic panels. The insulating ceramic panels include a plurality of hollow particles and an oxide binder. The plurality of hollow particles are formed from a hollow particle material that includes a metal oxide. The plurality of hollow particles defines an average equivalent particle diameter of at least 10 micrometers (µm) and at most 500 µm. In addition, the plurality of hollow particles defines an average wall thickness that is at least 3% and at most 30% of the average equivalent particle diameter. The oxide binder material attaches each hollow particle to at least one other hollow particle and differs from the hollow particle material. The insulating ceramic panels define a particle-enclosed void volume fraction, which is enclosed within the plurality of hollow particles, and an interstitial void volume fraction, which is defined within an interstitial space among the plurality of hollow particles.
C04B 35/63 - Préparation ou traitement des poudres individuellement ou par fournées utilisant des additifs spécialement adaptés à la formation des produits
B28B 1/00 - Fabrication d'objets façonnés à partir du matériau
B29C 67/24 - Techniques de façonnage non couvertes par les groupes , ou caractérisés par le choix de la matière
C04B 111/00 - Fonction, propriétés ou utilisation des mortiers, du béton ou de la pierre artificielle
A thermal expansion absorbing coupler configured to join individual pipes includes a multi-segment retaining shell having a V-shaped cross-section inner surface configured to draw together adjoining pipe ends. The coupler also includes a high-temperature material sealing ring configured to be arranged between the retaining shell and outer diameter of the adjoining pipes and block leakage of airflow from between the adjoining pipe ends. A test stand configured to position thereon an air cycling machine (ACM) having a compressor and a turbine may employ such a thermal expansion absorbing coupler. On the test stand, the coupler connects the ACM to a duct assembly and/or joins individual pipes of the duct assembly and absorbs thermal expansion of the duct assembly.
A test stand in operative communication with a source of conveyed air and configured to position thereon an air cycling machine (ACM) having a compressor and a turbine includes a support structure. The test stand also includes wheels mounted to the support structure and configured to facilitate mobility of the test stand. The test stand additionally includes a duct assembly moveably mounted to the support structure and configured to receive a flow of the conveyed air from an outlet of the source, supply the air to a compressor inlet of the ACM, and exhaust air from a turbine outlet of the ACM to atmosphere. The test stand also includes a pressure transducer configured to detect pressure of the conveyed air in the duct assembly and communicate the detected pressure to an electronic controller. The detected pressure is used by the electronic controller to regulate the source of conveyed air.
A testing arrangement includes an air heating and routing system (AHRS) system configured to receive and convey a flow of air and having a three-stage pressure adjusting subsystem for adjusting pressure of the conveyed air. The AHRS system also includes an air heater configured for regulating temperature of the conveyed air and plumbing for fluidly connecting the air heater and the three-stage pressure adjusting subsystem and convey the flow of air. The testing arrangement also includes a pressure transducer for detecting pressure of the conveyed air and an electronic controller. The electronic controller is configured to regulate the three-stage pressure adjusting subsystem, using the pressure detected by the pressure transducer, and the air heater to output the pressure and temperature regulated air via the AHRS plumbing. The testing arrangement may further include a test stand in operative communication with the AHRS. A testing method employs such a testing arrangement.
Testing coordination systems and a method of testing an aircraft are presented. A testing coordination system comprises a sequence coordination system stored on at least one sequence coordination server and configured to provide real-time reception and integration of data to provide communication between disparate systems while presenting a real-time changeable display.
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
G07C 5/12 - 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 sous forme de graphique
A device includes a receive antenna configured to receive a radar signal. The device includes a return signal generator configured to generate a return signal based on the received radar signal. The return signal includes at least a first component at a first frequency offset from a carrier frequency of the received radar signal and a second component at a second frequency offset from the carrier frequency. The device also includes a transmit antenna configured to transmit the return signal.
G01S 13/91 - Radar ou systèmes analogues, spécialement adaptés pour des applications spécifiques pour la commande du trafic
G01S 13/524 - Discrimination entre objets fixes et mobiles ou entre objets se déplaçant à différentes vitesses utilisant la transmission de trains discontinus d'ondes modulées par impulsions basée sur le décalage de phase ou de fréquence résultant du mouvement des objets, avec référence aux signaux transmis, p. ex. MTI cohérent
G01S 13/75 - Systèmes utilisant la reradiation d'ondes radio, p. ex. du type radar secondaireSystèmes analogues utilisant des transpondeurs alimentés par les ondes reçues, p. ex. utilisant des transpondeurs passifs
G01S 13/78 - Systèmes utilisant la reradiation d'ondes radio, p. ex. du type radar secondaireSystèmes analogues dans lesquels des signaux de type pulsé sont transmis effectuant la discrimination entre différents types de cibles, p. ex. radar pour l'identification ami–ennemi
30.
MODELING PATHOGEN TRANSMISSION IN A THREE-DIMENSIONAL ENVIRONMENT
A system for modeling pathogen transmission in a three-dimensional environment includes processing circuitry configured to implement a pathogen transmission modeling program stored in memory. The processing circuitry generates three-dimensional environment geometry and performs computational fluid dynamics to determine a three-dimensional vector field of air velocity vectors in the three-dimensional environment. Movements and properties of simulated persons within the three-dimensional environment are modeled and correlated with the three-dimensional vector field of air velocity vectors of the three-dimensional environment. The processing circuitry executes a dispersion model to simulate movement of a pathogen in the three-dimensional environment in accordance with the movements and properties of the simulated persons and the three-dimensional vector field of air velocity vectors. An epidemiological exposure model is executed to compute a risk of exposure of each simulated person, and an epidemiological infection model is executed to compute a risk of infection of each simulated person.
G06F 30/28 - Optimisation, vérification ou simulation de l’objet conçu utilisant la dynamique des fluides, p. ex. les équations de Navier-Stokes ou la dynamique des fluides numérique [DFN]
31.
MACHINE LEARNING-BASED ESTIMATION OF AIRCRAFT WEIGHT DISTRIBUTION
Examples are disclosed for estimating aircraft weight and center of gravity using a machine learning model. One example provides a computerized method, comprising receiving user input comprising data related to an aircraft, the data comprising an aircraft classification. The method further comprises obtaining parts data, determining an aircraft weight and a center of gravity for the aircraft based on the parts data, and outputting the aircraft weight and the center of gravity for the aircraft. Where parts data is omitted for one or more aircraft parts, a machine learning model comprising a clustering algorithm can be used to predict a weight and a location for the one or more aircraft parts. Examples are also disclosed for dynamically recomputing weight and center of gravity based on modifications to a digital model of the aircraft. The examples provide for secure storage of parts data without storing sensitive mission profile data.
Hinge mechanisms for a door of a fuselage of an aircraft, doors for a fuselage of an aircraft, aircraft that include the doors, and related methods. The hinge mechanisms include a plurality of components operatively attached to the fuselage via a body fitting. The doors include a hinge mechanism, an outer door panel, and an inner door panel and are configured to be selectively transitioned between a closed configuration, in which the door seals a door opening of the fuselage, and an open configuration, in which the door permits access to an interior of the fuselage via the door opening. The methods include methods of testing operation of the door and methods of actuating the door.
A vertical-takeoff-and-landing (VTOL) aircraft includes a plurality of navigation sensors and processing circuitry configured to implement a navigation system. The plurality of navigation sensors is configured to output navigation sensor data. The navigation system is configured to receive road map data, aviation map data, and navigation sensor data and execute an automated emergency landing control module. The automated emergency landing control module is configured to identify a plurality of candidate landing sites using the road map data, the aviation map data, and the navigation sensor data, and select a target landing site from among the plurality of candidate landing sites. Upon detection of an emergency condition, the automated emergency landing control module outputs the target landing site.
B64C 13/18 - Dispositifs amorçant la mise en œuvre actionnés automatiquement, p. ex. répondant aux détecteurs de rafales utilisant un pilote automatique
B64D 45/08 - Aides à l'atterrissageDispositifs de sécurité pour éviter la prise de sol brutale optiques
G05D 1/242 - Moyens basés sur la réflexion des ondes générées par le véhicule
G05D 1/245 - Dispositions pour déterminer la position ou l’orientation utilisant la navigation à l’estime
G05D 1/246 - Dispositions pour déterminer la position ou l’orientation utilisant des cartes d’environnement, p. ex. localisation et cartographie simultanées [SLAM]
G05D 1/248 - Dispositions pour déterminer la position ou l’orientation utilisant des signaux fournis par des sources artificielles extérieures au véhicule, p. ex. balises de navigation générés par des satellites, p. ex. GPS
A reinforcement film for a sandwich core, can include a removable layer; a removable adhesive layer; a reinforcement mesh; and an adhesive layer, wherein the removable adhesive layer is disposed on the removable layer and removably joins the removable layer to the reinforcement mesh, and wherein the adhesive layer is disposed on the reinforcement mesh and the adhesive layer is configured to permanently bond the reinforcement mesh to a sandwich core.
B32B 17/02 - Produits stratifiés composés essentiellement d'une feuille de verre ou de fibres de verre, de scorie ou d'une substance similaire sous forme de fibres ou filaments
B32B 7/06 - Liaison entre couches permettant une séparation sans difficultés
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
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
An air cycling machine (ACM) speed sensor assembly including a duct assembly connected to the ACM and configured to convey an airflow. The speed sensor assembly also includes a fiber-optic speed sensor arranged within the duct assembly, in line with the airflow, and proximate the ACM. The fiber-optic speed sensor is configured to detect rotational speed of the ACM and transmit a signal indicative of the detected rotational speed to an electronic controller. The speed sensor assembly may be employed on a test stand having a support structure with the duct assembly moveably mounted thereto.
G01P 3/36 - Dispositifs caractérisés par l'emploi de moyens optiques, p. ex. en utilisant la lumière infrarouge, visible ou ultraviolette
F25B 9/00 - Machines, installations ou systèmes à compression dans lesquels le fluide frigorigène est l'air ou un autre gaz à point d'ébullition peu élevé
F25B 9/06 - Machines, installations ou systèmes à compression dans lesquels le fluide frigorigène est l'air ou un autre gaz à point d'ébullition peu élevé utilisant des détendeurs
F25B 49/02 - Disposition ou montage des dispositifs de commande ou de sécurité pour machines, installations ou systèmes du type à compression
G01M 99/00 - Matière non prévue dans les autres groupes de la présente sous-classe
36.
COMPOSITE STRINGER PACKAGES AND SYSTEMS AND METHODS FOR CONSTRUCTING COMPOSITE STRINGER PACKAGES
A system for constructing a composite stringer package includes a tray, a lid, a deformable membrane, and a vacuum rig. The tray includes a receptacle. The lid is configured for moving relative to the tray between an open state and a closed state. The deformable membrane is configured for positioning over the tray. The vacuum rig is coupled to the tray. With the lid in the closed state, the lid and the tray are sealed together to form a sealed chamber. With the lid in the closed state, the deformable membrane is positioned in the sealed chamber between the tray and the lid. With the lid in the closed state, the vacuum rig is configured for applying vacuum to the sealed chamber.
B29C 70/44 - Façonnage ou imprégnation par compression pour la fabrication d'objets de longueur définie, c.-à-d. d'objets distincts utilisant une pression isostatique, p. ex. moulage par différence de pression, avec un sac à vide, dans un autoclave ou avec un caoutchouc expansible
B29C 70/54 - Parties constitutives, détails ou accessoiresOpérations auxiliaires
B29L 31/30 - Véhicules, p. ex. bateaux ou avions, ou éléments de leur carrosserie
37.
Display screen or portion thereof with animated graphical user interface
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.
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.
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
43.
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 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 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
52.
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
53.
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
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
59.
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 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.
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.
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.
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.
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.
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.
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.
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.
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
81.
LINE MANAGEMENT DEVICES, CABLE MANAGEMENT DEVICES AND METHODS FOR GUIDING LOCAL DISTRIBUTION OF UTILITY LINES
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
82.
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
85.
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
86.
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
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.
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.
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
96.
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.
