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Date
Nouveautés (dernières 4 semaines) 11
2022 juin (MACJ) 11
2022 mai 6
2022 avril 2
2022 mars 5
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Classe IPC
B64F 5/10 - Fabrication ou assemblage d’aéronefs, p.ex. gabarits à cet effet 148
B64D 47/00 - Equipements non prévus ailleurs 71
B64C 1/06 - Cadres; Lisses; Longerons 64
B64C 1/00 - Fuselages; Caractéristiques structurales communes aux fuselages, voilures, surfaces stabilisatrices ou organes apparentés 62
B64C 1/12 - Structure ou fixation de panneaux de revêtement 55
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Statut
En Instance 711
Enregistré / En vigueur 1 650
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1.

COMBINED MULTI-SPECTRAL AND POLARIZATION SENSOR

      
Numéro de document 03137651
Statut En instance
Date de dépôt 2021-11-04
Date de disponibilité au public 2022-06-19
Propriétaire THE BOEING COMPANY (USA)
Inventeur(s)
  • Gerwe, David Roderick
  • Idell, Paul S.
  • Paxton, Kevin Ray
  • Kunzler, Friedrich W.

Abrégé

A combined multi-spectral and polarization (CMSP) sensor is disclosed that enhances contrast-to-noise ratio (CNR). The CMSP sensor comprises a multi-spectral and polarization (MSP) filter, a single focal plane array (FPA), and a controller. The FPA comprises a plurality of detectors and the MSP filter comprises at least a first bandpass filter having a first frequency range and a second bandpass filter having a second frequency range that is distinct from the first frequency range and a first polarization filter having a first polarization value and a second polarization filter having a second polarization value that is distinct from the first polarization value.

Classes IPC  ?

  • G03B 11/00 - Filtres ou autres intercepteurs spécialement adaptés pour les besoins photographiques
  • G06V 10/24 - Alignement, centrage, détection de l’orientation ou correction de l’image
  • G01C 11/02 - Dispositions de prises de vues spécialement adaptées pour la photogrammétrie ou les levers photographiques, p.ex. pour commander le recouvrement des photos

2.

SYSTEMS AND METHODS FOR REAL-TIME NETWORK TRAFFIC ANALYSIS

      
Numéro de document 03139651
Statut En instance
Date de dépôt 2021-11-19
Date de disponibilité au public 2022-06-18
Propriétaire THE BOEING COMPANY (USA)
Inventeur(s)
  • Nobakht, Ramin
  • Sackman, Ronald Ward
  • Sullivan, Scott Charles

Abrégé

A system for detecting malicious traffic flows in a network is provided. The system includes a processor. Based on packet information received for a plurality of data packets transmitted over the network the processor is programmed to calculate inter- arrival times and packet durations for the plurality of data packets. The processor is also programmed to filter the packet information to remove noise. The processor is further programmed to generate at least one histogram based on the packet information, the inter-arrival times, and the packet durations. In addition, the processor is programmed to generate a power spectral density estimate based on the packet information, the inter-arrival times, and the packet durations. Moreover, the processor is programmed to analyze the at least one histogram and the power spectral density estimate to detect one or more unexpected data flows. Furthermore, the processor is programmed to report the one or more unexpected data flows.

Classes IPC  ?

  • H04L 43/062 - liés au trafic du réseau
  • H04L 43/08 - Surveillance ou test en fonction de métriques spécifiques, p.ex. la qualité du service [QoS], la consommation d’énergie ou les paramètres environnementaux
  • H04L 9/40 - Protocoles réseaux de sécurité
  • H04L 41/0894 - Gestion de la configuration du réseau basée sur des règles

3.

SYSTEMS AND METHODS FOR CONTEXT AWARE CYBERSECURITY

      
Numéro de document 03139589
Statut En instance
Date de dépôt 2021-11-18
Date de disponibilité au public 2022-06-18
Propriétaire THE BOEING COMPANY (USA)
Inventeur(s)
  • Sullivan, Scott Charles
  • Sackman, Ronald Ward
  • Nobakht, Ramin

Abrégé

A system that detects malicious traffic flows in a network includes a computer system including a processor in communication with at least one memory device. The processor is programmed to store a plurality of context information about the network including a plurality of devices. The processor is also programmed to determine a network configuration of the network at a specific point in time. The processor is further programmed to generate one or more security policies for one or more devices of the plurality of devices in the network based on the network configuration and the plurality of context information. In addition, the processor is programmed to deploy the one or more security policies to the one or more devices in the network, wherein the one or more devices are configured to execute an algorithm to monitor communications on the network in view of a corresponding security policy of the one or more security policies.

Classes IPC  ?

  • H04L 41/0894 - Gestion de la configuration du réseau basée sur des règles
  • H04L 9/40 - Protocoles réseaux de sécurité

4.

FAST BATTERY CHARGING METHOD AND SYSTEM FOR LARGE POWER LOAD APPLICATIONS

      
Numéro de document 03143037
Statut En instance
Date de dépôt 2021-12-17
Date de disponibilité au public 2022-06-18
Propriétaire THE BOEING COMPANY (USA)
Inventeur(s) Safai, Morteza

Abrégé

Renewable energy charging stations, systems, and methods are disclosed for capturing storing and delivering large amounts of renewable electrical energy from a renewable energy source to vehicles including passenger aircraft using charging circuits in communication with a demultiplexer and high-temperature superconducting cables to deliver required large electrical charges at fast charging rates safely and at low temperatures.

Classes IPC  ?

  • B60L 53/30 - PROPULSION DES VÉHICULES À TRACTION ÉLECTRIQUE; FOURNITURE DE L'ÉNERGIE ÉLECTRIQUE À L'ÉQUIPEMENT AUXILIAIRE DES VÉHICULES À TRACTION ÉLECTRIQUE; SYSTÈMES DE FREINS ÉLECTRODYNAMIQUES POUR VÉHICULES, EN GÉNÉRAL; SUSPENSION OU LÉVITATION MAGNÉTIQUES POUR VÉHICULES; CONTRÔLE DES PARAMÈTRES DE FONCTIONNEMENT DES VÉHICULES À TRACTION ÉLECTRIQUE; DISPOSITIFS ÉLECTRIQUES DE SÉCURITÉ POUR VÉHICULES À TRACTION ÉLECTRIQUE Échange d'éléments d’emmagasinage d'énergie dans les véhicules électriques - Détails de construction des stations de charge
  • B60L 53/50 - Stations de charge caractérisées par des moyens d’emmagasinage ou de production d'énergie
  • B60L 53/51 - Panneaux photovoltaïques
  • B60L 53/52 - Générateurs entraînés par le vent
  • B60L 53/60 - Surveillance et commande des stations de charge
  • H02J 7/00 - Circuits pour la charge ou la dépolarisation des batteries ou pour alimenter des charges par des batteries
  • H01B 12/00 - Conducteurs, câbles ou lignes de transmission supraconducteurs ou hyperconducteurs

5.

SATELLITE THERMAL ENCLOSURE

      
Numéro de document 03140350
Statut En instance
Date de dépôt 2021-11-24
Date de disponibilité au public 2022-06-17
Propriétaire THE BOEING COMPANY (USA)
Inventeur(s)
  • Aston, Richard W.
  • Woods, Emily Colleen
  • Zilz, Rachel Elizabeth
  • Langmack, Michael John
  • Hastings, Nicole Marie

Abrégé

A satellite assembly is disclosed, including a satellite and a shroud. The satellite is stowed in a launch vehicle and the shroud includes a frame supporting a flexible thermal blanket enclosing the satellite.

Classes IPC  ?

  • B64G 1/58 - Protection thermique, p.ex. boucliers thermiques

6.

STACKED SATELLITE ASSEMBLIES AND RELATED METHODS

      
Numéro de document 03140352
Statut En instance
Date de dépôt 2021-11-24
Date de disponibilité au public 2022-06-17
Propriétaire THE BOEING COMPANY (USA)
Inventeur(s)
  • Aston, Richard W.
  • Woods, Emily Colleen
  • Zilz, Rachel Elizabeth
  • Langmack, Michael John
  • Hastings, Nicole Marie

Abrégé

A satellite apparatus is disclosed, including a housing having first and second opposing walls, and a support structure inside the housing spanning the first and second walls. The support structure is structurally connected to the housing only at the first and second walls, and an end portion of the support structure is configured for connection to a launch vehicle by a separation system.

Classes IPC  ?

  • B64G 1/10 - Satellites artificiels; Systèmes de tels satellites; Véhicules interplanétaires
  • B64G 1/22 - Parties de véhicules spatiaux ou équipements spécialement destinés à être fixés dans ou sur ces véhicules
  • B64G 1/64 - Systèmes pour réunir ou séparer des véhicules spatiaux ou des parties de ceux-ci, p.ex. aménagement pour l'accostage ou l'amarrage

7.

STRUCTURAL INCONSISTENCY DETECTION USING DISTANCE DATA

      
Numéro de document 03140347
Statut En instance
Date de dépôt 2021-11-24
Date de disponibilité au public 2022-06-17
Propriétaire THE BOEING COMPANY (USA)
Inventeur(s)
  • Erdim, Huseyin
  • Ortiz, Alejandro Alberto
  • Drumheller, Michael
  • Walker, Eric James

Abrégé

Methods and systems for computing distance data for a structure. A scan surface that represents an inspection area of the structure is identified. A plurality of sample points on an outer surface identified from a model of the structure and a corresponding plurality of projected points on an inner surface identified from the model of the structure are generated using the scan surface, a first geometric representation of the outer surface, and a second geometric representation of the inner surface. Distance data is computed using the plurality of sample points and the corresponding plurality of projected points. The distance data identifies a distance between a point pair formed by a sample point of the plurality of sample points and a corresponding projected point of the corresponding plurality of projected points.

Classes IPC  ?

  • G01B 21/30 - Dispositions pour la mesure ou leurs détails pour autant qu'ils ne soient pas adaptés à des types particuliers de moyens de mesure faisant l'objet des autres groupes de la présente sous-classe pour mesurer la rugosité ou l'irrégularité des surfaces
  • B64F 5/60 - Test ou inspection des composants ou des systèmes d'aéronefs
  • G01B 17/08 - Dispositions pour la mesure caractérisées par l'utilisation de vibrations infrasonores, sonores ou ultrasonores pour mesurer la rugosité ou l'irrégularité des surfaces
  • G01B 21/20 - Dispositions pour la mesure ou leurs détails pour autant qu'ils ne soient pas adaptés à des types particuliers de moyens de mesure faisant l'objet des autres groupes de la présente sous-classe pour mesurer des contours ou des courbes, p.ex. pour déterminer un profil

8.

METHODS AND BRAKE SYSTEMS TO REDUCE BRAKE WEAR DURING AIRCRAFT TAXIING FIELD

      
Numéro de document 03129798
Statut En instance
Date de dépôt 2021-09-02
Date de disponibilité au public 2022-06-16
Propriétaire THE BOEING COMPANY (USA)
Inventeur(s) Miller, Trent Daryl

Abrégé

Methods for reducing brake wear during aircraft taxiing are disclosed. As one example, a method comprises determining a sequence to apply brakes of a given set of landing gear during a brake event, wherein the determining includes selecting a warmer brake of the brakes to initially apply at a start of the brake event, and selecting a cooler brake of the brakes to subsequently apply when the warmer brake is released during the brake event. The method further comprises applying the warmer brake and the cooler brake in the determined sequence during the brake event. In another example, an aircraft brake system comprises brakes and a controller that is programmed to, during taxiing, apply a warmer subset of the brakes before applying a cooler subset of the brakes during a brake event.

Classes IPC  ?

  • B64C 19/00 - Dispositifs de commande des aéronefs non prévus ailleurs
  • B60T 8/171 - Détection des paramètres utilisés pour la régulation; Mesure des valeurs utilisées pour la régulation
  • B60T 17/22 - Dispositifs pour surveiller ou vérifier les systèmes de freins; Dispositifs de signalisation
  • B64C 25/42 - Aménagement ou adaptation des freins

9.

TRIM ACTUATORS FOR HORIZONTAL STABILIZERS AND METHODS OF CONTROLLING HORIZONTAL STABILIZERS

      
Numéro de document 03134354
Statut En instance
Date de dépôt 2021-10-15
Date de disponibilité au public 2022-06-16
Propriétaire THE BOEING COMPANY (USA)
Inventeur(s)
  • Rozeboom, Aaron M.
  • Parks, Morgan S.

Abrégé

A trim actuator (102) for a horizontal stabilizer (210) comprises a power screw (106), a rotary actuator (104), configured to rotate the power screw (106), and a nut (108), configured to translate along the power screw (106) when the power screw (106) is rotated. Trim actuator (102) also comprises an anti-back-drive mechanism (114), configured to prevent the power screw (106) from rotating in a first rotational direction when a first force is applied to the nut (108) in a first axial direction and to prevent the power screw (106) from rotating in a second rotational direction, opposite the first rotational direction, when a second force is applied to the nut (108) in a second axial direction. Trim actuator (102) further comprises a sensor (120), configured to measure internal loading of the anti-back-drive mechanism (114) when the first force is applied to the nut (108) in the first axial direction or when the second force is applied to the nut (108) in the second axial direction.

Classes IPC  ?

  • B64C 13/34 - Dispositifs de transmission sans amplification de puissance ou dans les cas où l'amplification de puissance est sans objet mécaniques utilisant des engrenages
  • B64F 5/60 - Test ou inspection des composants ou des systèmes d'aéronefs
  • B64C 5/02 - Plans fixes horizontaux
  • B64C 5/16 - Surfaces stabilisatrices réglables autour d'axes orientés dans le sens de l'envergure
  • F16D 7/02 - Accouplements à glissement, p.ex. glissant en cas de surcharge, pour absorber les chocs du type à friction
  • F16D 67/00 - Combinaisons d'accouplements et de freins; Combinaisons d'embrayages et de freins

10.

QUANTIUM PARALLEL EVENT COUNTER

      
Numéro de document 03137241
Statut En instance
Date de dépôt 2021-10-29
Date de disponibilité au public 2022-06-10
Propriétaire THE BOEING COMPANY (USA)
Inventeur(s) Ray, Gary A.

Abrégé

A method, apparatus, and system for counting events. a set of quantum registers is reset. A Hadamard operator is applied to the set of quantum registers. A quantum instruction is executed on the set of quantum registers, wherein the quantum instruction incorporates a function for an event vector comprising events identified by bits. The Hadamard operator is applied to the set of quantum registers after executing the quantum instruction. The set of quantum registers is measured to form a measurement of the set of quantum registers. An approximate count of the events is determined using the measurement of the set of quantum registers.

Classes IPC  ?

  • G06N 10/60 - Algorithmes quantiques, p.ex. fondés sur l'optimisation quantique ou les transformées quantiques de Fourier ou de Hadamard

11.

DEBUG TRACE STREAMS FOR CORE SYNCHRONIZATION

      
Numéro de document 03136322
Statut En instance
Date de dépôt 2021-10-27
Date de disponibilité au public 2022-06-02
Propriétaire THE BOEING COMPANY (USA)
Inventeur(s)
  • Haldeman, David P.
  • Miller, Eric J.

Abrégé

The present disclosure provides for synchronization of multi-core systems by monitoring a plurality of debug trace data streams for a redundantly operating system including a corresponding plurality of cores performing a task in parallel; in response to detecting a state difference on one debug trace data stream of the plurality of debug trace data streams relative to other debug trace data streams of the plurality of debug trace data streams: marking a given core associated with the one debug trace data stream as an affected core; and restarting the affected core.

Classes IPC  ?

  • G06F 11/30 - Surveillance du fonctionnement
  • G06F 11/36 - Prévention d'erreurs en effectuant des tests ou par débogage de logiciel
  • G06F 15/16 - Associations de plusieurs calculateurs numériques comportant chacun au moins une unité arithmétique, une unité programme et un registre, p.ex. pour le traitement simultané de plusieurs programmes

12.

MOBILE COMMUNICATION SYSTEM EMPLOYING ACTIVE BANDWIDTH MANAGEMENT

      
Numéro de document 03131473
Statut En instance
Date de dépôt 2021-09-21
Date de disponibilité au public 2022-05-17
Propriétaire THE BOEING COMPANY (USA)
Inventeur(s)
  • Kumar, Anil
  • Phillips, David
  • Reinbold, Michael G.

Abrégé

A mobile communication system for sending data to one or more satellite resources over a wireless connection includes one or more processors and a memory coupled to the processors. The memory stores data into a database and program code that, when executed by the processors, causes the mobile communication system to receive a primary service data stream and a secondary service data stream, and determine a bandwidth utilization efficiency of the wireless connection between the mobile communication system and the one or more satellite resources. In response to determining the wireless connection has available headroom, the primary service data stream is combined with the secondary service data stream to create an aggregated data packet. In response to determining the aggregated data packet is less than or equal to the size of the available headroom, the mobile communication system transmits the aggregated data packet over the wireless connection.

Classes IPC  ?

  • H04L 47/36 - en déterminant la taille des paquets, p.ex. l’unité de transfert maximale [MTU]
  • H04W 40/06 - Sélection d'itinéraire ou de voie de communication, p.ex. routage basé sur l'énergie disponible ou le chemin le plus court sur la base des ressources nodales sans fil sur la base des caractéristiques des antennes disponibles
  • H04W 72/04 - Affectation de ressources sans fil

13.

INTERNET OF THINGS LABEL FOR FACTORY AND WAREHOUSE APPLICATIONS

      
Numéro de document 03128356
Statut En instance
Date de dépôt 2021-08-16
Date de disponibilité au public 2022-05-13
Propriétaire THE BOEING COMPANY (USA)
Inventeur(s)
  • Williams, John Dalton
  • Mitchell, Michael Francis

Abrégé

Systems, apparatuses and methods may provide for label technology that includes a flexible substrate and a flexible circuit coupled to the flexible substrate, the flexible circuit including a power source, a microcontroller, a plurality of sensors, one or more transceivers, and an antenna. The microcontroller may be configured to identify sensor readings in one or more signals from the plurality of sensors and send the sensor readings to one or more of a central computer or a computer network via one or more standard wireless transmission protocols, wherein at least one of the sensor readings is sent in a push communication.

Classes IPC  ?

  • G09F 3/02 - Formes ou structures
  • H04W 4/38 - Services spécialement adaptés à des environnements, à des situations ou à des fins spécifiques pour la collecte d’informations de capteurs
  • G16Y 20/10 - Information détectée ou collectée par les objets relative à l’environnement, p.ex. la température; relative à l’emplacement
  • G16Y 40/10 - Détection; Surveillance
  • G01K 1/024 - Moyens d’indication ou d’enregistrement spécialement adaptés aux thermomètres pour l’indication à distance
  • G01N 37/00 - RECHERCHE OU ANALYSE DES MATÉRIAUX PAR DÉTERMINATION DE LEURS PROPRIÉTÉS CHIMIQUES OU PHYSIQUES - Détails non couverts par les autres groupes de la présente sous-classe
  • G05B 19/042 - Commande à programme autre que la commande numérique, c.à d. dans des automatismes à séquence ou dans des automates à logique utilisant des processeurs numériques
  • H05K 1/02 - Circuits imprimés - Détails
  • H04W 80/00 - Protocoles de réseaux sans fil ou adaptations de protocoles à un fonctionnement sans fil

14.

FLIGHT CONTROL SURFACE ACTUATION SYSTEMS INCLUDING SKEW DETECTION SYSTEMS, AND ASSOCIATED METHODS

      
Numéro de document 03131175
Statut En instance
Date de dépôt 2021-09-16
Date de disponibilité au public 2022-05-10
Propriétaire THE BOEING COMPANY (USA)
Inventeur(s) Mitchell, Ira, Iii

Abrégé

Flight control surface actuation systems including skew detection systems and associated methods. A flight control surface actuation system includes a skew detection system configured to generate a skew detection signal that represents a skew condition of a flight control surface. In some examples, the skew detection system includes a skew lanyard and a detection mechanism assembly (DMA) configured to detect a lanyard displacement of the skew lanyard and to generate an analog lanyard displacement signal. In some examples, the skew detection system includes a hybrid sensing actuator that includes an actuator output and an actuator output position sensor directly coupled to the actuator output. Methods of utilizing a flight control surface actuation system include detecting a skew condition in the flight control surface utilizing DMAs and/or hybrid sensing actuators.

Classes IPC  ?

  • B64C 13/24 - Dispositifs de transmission
  • B64C 3/50 - Variation de la courbure par volets de bord d'attaque ou de bord de fuite

15.

ELECTRON BEAM LITHOGRAPHY WITH A BILAYER RESIST

      
Numéro de document 03130856
Statut En instance
Date de dépôt 2021-09-14
Date de disponibilité au public 2022-05-05
Propriétaire THE BOEING COMPANY (USA)
Inventeur(s)
  • Mei, Antonio
  • Milosavljevic, Ivan
  • Simpson, Amanda

Abrégé

A method, apparatus, and system for processing a material stack. A hydrogen silsesquioxane layer is deposited on the material stack. A diffusion barrier layer is deposited on the hydrogen silsesquioxane layer to form a bilayer. The diffusion barrier layer comprises a material having a thickness that increases an amount of time before the hydrogen silsesquioxane layer ages to change a dose in an electron beam needed to expose the hydrogen silsesquioxane layer for a selected feature geometry with a desired width. The electron beam is directed through a surface of the bilayer to form an exposed portion of the bilayer and applies the dose that is selected based on a pattern density of features for the material stack to have a desired level of exposure of the hydrogen silsesquioxane layer for the selected feature geometry. The hydrogen silsesquioxane layer is developed. The exposed portion remains on material stack.

Classes IPC  ?

  • H01L 21/02 - Fabrication ou traitement des dispositifs à semi-conducteurs ou de leurs parties constitutives
  • H01L 29/12 - Corps semi-conducteurs caractérisés par les matériaux dont ils sont constitués
  • H01L 39/24 - Procédés ou appareils spécialement adaptés à la fabrication ou au traitement des dispositifs couverts par  ou de leurs parties constitutives

16.

SYSTEM AND METHOD FOR SECURING A LONGERON TO A WING AND FUSELAGE OF AN AIRCRAFT

      
Numéro de document 03129864
Statut En instance
Date de dépôt 2021-09-02
Date de disponibilité au public 2022-05-03
Propriétaire THE BOEING COMPANY (USA)
Inventeur(s)
  • Keefe, Drew-Daniel T.
  • Hollowell, Jeff S.

Abrégé

A system and a method for securing a portion of a fuselage of an aircraft to a portion of a wing of the aircraft include a longeron having a first end and a second end, a first moveable coupling interface that moveably secures the first end to the portion of the fuselage, and a second moveable coupling interface that moveably secures the second end to the portion of the wing.

Classes IPC  ?

  • B64C 1/26 - Fixation de la voilure, des empennages ou des surfaces stabilisatrices

17.

COMPRESSION FITTING WITH VISUAL TORQUE INDICATOR

      
Numéro de document 03137413
Statut En instance
Date de dépôt 2021-11-02
Date de disponibilité au public 2022-05-03
Propriétaire THE BOEING COMPANY (USA)
Inventeur(s)
  • Coffland, Donald Wayne
  • Coello, Ryan Kody
  • Clements, Andrew Benjamin
  • Clements, Ronald Lawrence
  • Tom, Christian James
  • Linnenkamp, David James

Abrégé

A tubing nut fastener is described that includes two separate elements that are partially rotatable with respect to each other. In between the rotatable elements, engagement members (e.g., balls) are captured within interior channels. Both of the partially rotatable elements include a permanent marking or other non-removable visual indicator, which varies spatially depending on whether the tubing nut fastener is in a torqued state or an un-torqued state, thereby providing a simple visual indication of the status of the tubing nut fastener.

Classes IPC  ?

  • F16L 19/00 - Raccords dans lesquels les surfaces d'étanchéité sont maintenues en contact par un organe, p.ex. un écrou à oreilles vissé dans, ou vissé sur une des parties du raccord
  • F16L 25/00 - Structure ou détails de raccords de tuyaux non prévus dans les groupes ou présentant in intérêt autre que celui visé par ces groupes

18.

INTEGRATED ELECTRIC PROPULSION UNIT

      
Numéro de document 03133673
Statut En instance
Date de dépôt 2021-10-08
Date de disponibilité au public 2022-04-20
Propriétaire THE BOEING COMPANY (USA)
Inventeur(s)
  • Lacaux, Frederic
  • Karimi, Kamiar J.
  • Solodovnik, Eugene V.
  • Kutzmann, Aaron
  • Darmstadt, Patrick R.
  • Beckman, Mary E.
  • Silva, Alejandro
  • Silveri, Nicholas J.
  • Zidovetzki, Esther S.

Abrégé

An electric propulsion unit comprising a housing, an AC motor, a beta rod, a propeller, a governor, an inverter, and a controller. The AC motor is disposed within the housing and includes a plurality of bearings supported inside the housing, a hollow motor shaft rotatably coupled to the housing by the plurality of bearings, a stator which is supported by the housing, and a rotor which is mounted to the hollow motor shaft. The beta rod is axially translatable inside the hollow motor shaft. The propeller is mechanically coupled to the hollow motor shaft. The propeller includes propeller blades having an adjustable pitch angle which depends on an axial position of the beta rod. The governor is configured to adjust a pitch angle of the propeller blades by actuating axial translation of the beta rod. The inverter is disposed within the housing and connected to receive DC power for conversion into AC power. The controller is disposed inside the housing and configured to control operation of the inverter and control the pitch angle of the propeller blades.

Classes IPC  ?

  • B64D 27/24 - Aéronefs caractérisés par le type ou la position des groupes moteurs utilisant la vapeur, l'électricité ou l'énergie de ressorts
  • H02K 11/33 - Circuits d’entraînement, p.ex. circuits électroniques de puissance
  • B64C 11/30 - Mécanismes de changement de pas des pales
  • B64D 31/00 - Commande des groupes moteurs; Leur disposition
  • B64D 33/00 - Aménagement sur les aéronefs des éléments ou des auxiliaires des ensembles fonctionnels de propulsion, non prévu ailleurs
  • B64D 35/02 - Transmission de la puissance du groupe moteur aux hélices ou aux rotors; Aménagements des transmissions caractérisée par le type de groupe moteur
  • H02K 7/14 - Association structurelle à des charges mécaniques, p.ex. à des machines-outils portatives ou des ventilateurs
  • H02K 11/00 - Association structurelle de machines dynamo-électriques à des organes électriques ou à des dispositifs de blindage, de surveillance ou de protection

19.

THERMAL TRANSFER BLANKET SYSTEM

      
Numéro de document 03144382
Statut En instance
Date de dépôt 2021-10-18
Date de disponibilité au public 2022-04-20
Propriétaire THE BOEING COMPANY (USA)
Inventeur(s) Dichiara, Robert A.

Abrégé

A thermal transfer blanket includes a flexible container comprising a thermally insulating material. A thermal energy storage media is disposed within the flexible container.

Classes IPC  ?

  • H05B 3/34 - Eléments chauffants ayant une surface s'étendant essentiellement dans deux dimensions, p.ex. plaques chauffantes flexibles, p.ex. grillages ou tissus chauffants
  • B64F 5/40 - Entretien ou réparation d’aéronefs

20.

AIRCRAFT FUSELAGE LONGITUDINAL SPLICE FOR JOINING HALF BARREL FUSELAGE SECTIONS AND OTHER SPLICED FUSELAGE SECTIONS

      
Numéro de document 03128351
Statut En instance
Date de dépôt 2021-08-16
Date de disponibilité au public 2022-03-30
Propriétaire THE BOEING COMPANY (USA)
Inventeur(s)
  • Stoddard, Zachary N.
  • Mcghee, Ronald L.

Abrégé

An aircraft fuselage body is constructed of an upper body section having a curved cross- section configuration and a lower body section having a curved cross-section configuration. The upper body section and the lower body section are joined together to form an aircraft fuselage body by splice straps that are secured, end to end along interior surfaces of the upper body section and the lower body section. The aircraft fuselage body being constructed of an upper body section and a lower body section enables installation of systems separately into the upper body section and the lower body section prior to the upper body section and lower body section being joined together.

Classes IPC  ?

  • B64C 1/00 - Fuselages; Caractéristiques structurales communes aux fuselages, voilures, surfaces stabilisatrices ou organes apparentés
  • F16B 5/00 - Jonction de feuilles ou de plaques soit entre elles soit à des bandes ou barres parallèles à elles

21.

SYSTEMS AND METHODS OF UV CLEANING

      
Numéro de document 03132461
Statut En instance
Date de dépôt 2021-09-29
Date de disponibilité au public 2022-03-30
Propriétaire THE BOEING COMPANY (USA)
Inventeur(s) Mcintosh, Darren C.

Abrégé

The present disclosure provides a system including an ultraviolet (UV) light source, a power source configured to provide power to the UV light source, and a photochromatic indicator associated with a component, the photochromatic indicator being in a first state, the UV light source being configured to change the photochromatic indicator from a first state to a second state, the second state indicating that the component has been cleaned, the second state being visible to a naked eye under ambient lighting.

Classes IPC  ?

  • A61L 2/10 - Procédés ou appareils de désinfection ou de stérilisation de matériaux ou d'objets autres que les denrées alimentaires ou les lentilles de contact; Accessoires à cet effet utilisant des phénomènes physiques des radiations des ultraviolets
  • A61L 2/28 - Dispositifs pour tester l'efficacité ou l'intégralité de la stérilisation, p.ex. indicateurs qui changent de couleur

22.

PROTECTION SYSTEM FOR AIRCRAFT ELECTRIC PROPULSION MOTOR AND MOTOR CONTROLLER

      
Numéro de document 03129793
Statut En instance
Date de dépôt 2021-09-02
Date de disponibilité au public 2022-03-20
Propriétaire THE BOEING COMPANY (USA)
Inventeur(s)
  • Lacaux, Frederic
  • Solodovnik, Eugene V.
  • Khozikov, Vyacheslav

Abrégé

A method for protecting an electric propulsion system in response to occurrence of a fault. The method includes the step of activating short circuits in power switches of inverters in a motor controller to redirect current regenerated by a motor which is electrically coupled to the motor controller and mechanically coupled to a propeller. The method further includes feathering the propeller while the motor is regenerating current. The protection logic is designed to address different types of faults, including faults in the high-voltage direct-current bus, faults in the motor controller, and faults in the motor.

Classes IPC  ?

  • H02P 29/024 - Détection d’un défaut, p.ex. court circuit, rotor bloqué, circuit ouvert ou perte de charge
  • B64D 27/24 - Aéronefs caractérisés par le type ou la position des groupes moteurs utilisant la vapeur, l'électricité ou l'énergie de ressorts
  • B64D 31/00 - Commande des groupes moteurs; Leur disposition
  • H02P 27/06 - Dispositions ou procédés pour la commande de moteurs à courant alternatif caractérisés par le type de tension d'alimentation utilisant une tension d’alimentation à fréquence variable, p.ex. tension d’alimentation d’onduleurs ou de convertisseurs utilisant des convertisseurs de courant continu en courant alternatif ou des onduleurs

23.

MACHINE LEARNING NETWORK FOR SCREENING QUANTUM DEVICES

      
Numéro de document 03126479
Statut En instance
Date de dépôt 2021-07-29
Date de disponibilité au public 2022-03-18
Propriétaire THE BOEING COMPANY (USA)
Inventeur(s) Mei, Antonio Rodolph Bighetti

Abrégé

A method, apparatus, system, and computer program product for screening quantum devices. A computer system sends features extracted from an image of a quantum device into a classification neural network. The classification neural network is configured to identify a set of characteristics for the quantum device from a group of mutually exclusive characteristics based on the features identified in the image of the quantum device and output the set of characteristics identified for the quantum device. The computer system receives the set of characteristics identified by the classification neural network for the quantum devices. The set of characteristics indicates whether the quantum devices will function as desired.

Classes IPC  ?

  • G06N 10/00 - Calculateurs quantiques, c. à d. systèmes de calculateurs basés sur des phénomènes de mécanique quantique
  • G06V 10/764 - utilisant la classification, p.ex. des objets vidéo
  • G06V 10/82 - utilisant les réseaux neuronaux
  • G06N 3/02 - Systèmes de calculateurs basés sur des modèles biologiques utilisant des modèles de réseaux neuronaux
  • G06N 3/08 - Méthodes d'apprentissage

24.

VIRTUAL MACHINE FOR VIRTUALIZING GRAPHICS FUNCTIONS

      
Numéro de document 03123272
Statut En instance
Date de dépôt 2021-06-25
Date de disponibilité au public 2022-03-15
Propriétaire THE BOEING COMPANY (USA)
Inventeur(s)
  • Dale, Timothy James
  • Hotra, Jonathan Nicholas
  • Patterson, Glenn Alan
  • Sowadski, Craig

Abrégé

A host computer for emulating a target system includes a host memory, a CPU, and a host GPU. The host memory is configured to store a library of graphics functions and a VM. The VM includes a section of emulated memory storing target code configured to execute on the target system. The CPU is configured to execute the VM to emulate the target system. The VM is configured to execute the target code and intercept a graphics function call in the target code. The VM is further configured to redirect the graphics function call to a corresponding graphics function in the library of graphics functions stored in the host memory. The host GPU is configured to execute the corresponding graphics function to determine at least one feature configured to be rendered on a display coupled to the host GPU.

Classes IPC  ?

  • G06F 9/455 - Dispositions pour exécuter des programmes spécifiques Émulation; Interprétation; Simulation de logiciel, p.ex. virtualisation ou émulation des moteurs d’exécution d’applications ou de systèmes d’exploitation
  • G06F 9/448 - Paradigmes d’exécution, p.ex. implémentation de paradigmes de programmation

25.

SYSTEM AND METHOD FOR ALLOCATING PROPULSION LOAD POWER DRAWN FROM HIGH-ENERGY AND HIGH-POWER BATTERIES

      
Numéro de document 03129214
Statut En instance
Date de dépôt 2021-08-27
Date de disponibilité au public 2022-02-28
Propriétaire THE BOEING COMPANY (USA)
Inventeur(s)
  • Trela, John A.
  • Barekatein, Mehdy
  • Brown, Glen M.
  • Liu, Shengyi

Abrégé

System and method for allocating load power drawn from multiple batteries for powering propulsion of a vehicle. The system includes: high- energy and high-power batteries respectively designed for optimal production of DC power during high-specific-energy and high-specific-power propulsion; and battery health management systems configured to monitor state of charge and state of health of the batteries and generate battery status signals. The system further includes a propulsion load configured to produce propulsion force using power converted from power generated by at least one of the batteries and a system controller configured to allocate load power drawn from the high-energy and high-power batteries for use by the propulsion load in dependence on a propulsion phase of the vehicle and the battery status.

Classes IPC  ?

  • B60L 58/10 - Procédés ou agencements de circuits pour surveiller ou commander des batteries ou des piles à combustible, spécialement adaptés pour des véhicules électriques pour la surveillance et la commande des batteries
  • B60L 50/51 - Propulsion électrique par source d'énergie intérieure au véhicule utilisant de la puissance de propulsion fournie par des batteries ou des piles à combustible caractérisée par des moteurs à courant alternatif
  • B60L 50/60 - Propulsion électrique par source d'énergie intérieure au véhicule utilisant de la puissance de propulsion fournie par des batteries ou des piles à combustible utilisant de l'énergie fournie par des batteries
  • B60L 58/16 - Procédés ou agencements de circuits pour surveiller ou commander des batteries ou des piles à combustible, spécialement adaptés pour des véhicules électriques pour la surveillance et la commande des batteries en fonction du vieillissement de la batterie, p.ex. du nombre de cycles de charge ou de l'état de santé [SoH]
  • B60L 15/02 - Procédés, circuits ou dispositifs pour commander la propulsion des véhicules à traction électrique, p.ex. commande de la vitesse des moteurs de traction en vue de réaliser des performances désirées; Adaptation sur les véhicules à traction électrique de l'installation de commande à distance à partir d'un endroit fixe, de différents endroits du véhicule ou de différents véhicules d'un même train caractérisés par la forme du courant utilisé dans le circuit de commande
  • B60L 15/20 - Procédés, circuits ou dispositifs pour commander la propulsion des véhicules à traction électrique, p.ex. commande de la vitesse des moteurs de traction en vue de réaliser des performances désirées; Adaptation sur les véhicules à traction électrique de l'installation de commande à distance à partir d'un endroit fixe, de différents endroits du véhicule ou de différents véhicules d'un même train pour la commande du véhicule ou de son moteur en vue de réaliser des performances désirées, p.ex. vitesse, couple, variation programmée de la vitesse
  • B64D 27/24 - Aéronefs caractérisés par le type ou la position des groupes moteurs utilisant la vapeur, l'électricité ou l'énergie de ressorts
  • H01M 10/48 - Accumulateurs combinés à des dispositions pour mesurer, tester ou indiquer l'état des éléments, p.ex. le niveau ou la densité de l'électrolyte
  • H02J 7/00 - Circuits pour la charge ou la dépolarisation des batteries ou pour alimenter des charges par des batteries
  • G01R 31/382 - Dispositions pour la surveillance de variables des batteries ou des accumulateurs, p.ex. état de charge
  • G01R 31/392 - Détermination du vieillissement ou de la dégradation de la batterie, p.ex. état de santé

26.

VIRTUAL MACHINE FOR DEVELOPING AND TESTING TARGET CODE FOR HARDWARE DESIGNS

      
Numéro de document 03123074
Statut En instance
Date de dépôt 2021-06-22
Date de disponibilité au public 2022-02-26
Propriétaire THE BOEING COMPANY (USA)
Inventeur(s) Hotra, Jonathan Nicholas

Abrégé

A host computer includes a memory storing a proxy VM, and a host CPU. The proxy VM emulates target hardware having an incomplete design. The proxy VM includes a virtual processor for emulating a target processor. The proxy VM includes an emulated memory coupled to the virtual processor over a virtual memory bus. The emulated memory includes at least one portion storing the target code. The host CPU is configured to execute the proxy VM to emulate the target hardware. The proxy VM, upon execution by the host CPU, is configured to execute, by the virtual processor, the target code.

Classes IPC  ?

  • G06F 9/455 - Dispositions pour exécuter des programmes spécifiques Émulation; Interprétation; Simulation de logiciel, p.ex. virtualisation ou émulation des moteurs d’exécution d’applications ou de systèmes d’exploitation
  • G06F 9/445 - Chargement ou démarrage de programme
  • G06F 11/36 - Prévention d'erreurs en effectuant des tests ou par débogage de logiciel

27.

FLEXIBLE CIRCUIT FOR SOLAR CELL ASSEMBLIES

      
Numéro de document 03127970
Statut En instance
Date de dépôt 2021-08-11
Date de disponibilité au public 2022-02-21
Propriétaire THE BOEING COMPANY (USA)
Inventeur(s) Fetzer, Christopher M.

Abrégé

A solar cell assembly having a flexible circuit is described. The solar cell assembly includes a solar cell having a solar-facing surface and a non-solar- facing surface, the solar cell comprising a cell corner. The solar cell assembly further includes a flexible circuit coupled to the non-solar-facing surface of the solar. The flexible circuit is substantially coextensive with the solar cell. The flexible circuit includes a flexible insulator including a plurality of edges aligned with the solar cell, a flexible corner extending past the cell corner, and a flexible tab extending from an edge of the plurality of edges. The flexible circuit includes a circuit substantially embedded in the flexible insulator. The circuit comprises a first electric contact exposed at a solar- facing side of the flexible corner, and a second electric contact exposed at a solar-facing side of the flexible tab.

Classes IPC  ?

  • H01L 31/02 - Dispositifs à semi-conducteurs sensibles aux rayons infrarouges, à la lumière, au rayonnement électromagnétique d'ondes plus courtes, ou au rayonnement corpusculaire, et spécialement adaptés, soit comme convertisseurs de l'énergie dudit rayonnement e; Procédés ou appareils spécialement adaptés à la fabrication ou au traitement de ces dispositifs ou de leurs parties constitutives; Leurs détails - Détails
  • H01L 25/03 - Ensembles consistant en une pluralité de dispositifs à semi-conducteurs ou d'autres dispositifs à l'état solide les dispositifs étant tous d'un type prévu dans le même sous-groupe des groupes , p.ex. ensembles de diodes redresseuses

28.

CFRP FUSELAGE FRAME WITH SECUREMENT TO VERTICAL TAIL FIN

      
Numéro de document 03123712
Statut En instance
Date de dépôt 2021-06-30
Date de disponibilité au public 2022-02-12
Propriétaire THE BOEING COMPANY (USA)
Inventeur(s)
  • Diep, Paul
  • Pham, Phiyen T.

Abrégé

A securement assembly for securing a vertical tail fin assembly to an aircraft includes a first lug member secured to the vertical tail fin assembly. The securement assembly further includes a first clevis member. The first clevis member includes a first end portion of the first clevis member is engaged to the first lug member. A second end portion of the first clevis member is secured to a first fuselage frame constructed of a composite material with a first fastener which extends through the second end portion and the first fuselage frame in a first direction transverse to the first fuselage frame.

Classes IPC  ?

  • B64C 1/26 - Fixation de la voilure, des empennages ou des surfaces stabilisatrices
  • B64C 1/06 - Cadres; Lisses; Longerons

29.

FEED-THROUGH WIRING SOLUTION FOR SOLAR CELL MODULES

      
Numéro de document 03124504
Statut En instance
Date de dépôt 2021-07-13
Date de disponibilité au public 2022-02-11
Propriétaire THE BOEING COMPANY (USA)
Inventeur(s) Bardfield, Rina S.

Abrégé

The present disclosure provides a solar cell module, comprising (a) a laminate substrate having a first surface and a second surface opposite the first surface, (b) a solar cell positioned on the first surface of the laminate substrate, (c) a first contact pad positioned on the first surface of the laminate substrate adjacent to the solar cell, (d) a second contact pad positioned on the second surface of the laminate substrate, (e) one or more vias positioned through the laminate substrate to electrically connect the first contact pad to the second contact pad, and (f) one or more interconnects extending from the solar cell and electrically coupling the solar cell to the first contact pad.

Classes IPC  ?

  • H02S 40/34 - Composants électriques comprenant une connexion électrique structurellement associée au module PV, p.ex. boîtes de jonction
  • H02S 40/20 - Composants optiques
  • H02S 40/36 - Composants électriques caractérisés par des moyens d'interconnexions électriques spéciaux entre plusieurs modules PV, p.ex. connexion électrique module à module
  • H01L 31/042 - Modules PV ou matrices de cellules PV individuelles

30.

AIRCRAFT SYSTEM OPERATIONAL TESTING

      
Numéro de document 03127362
Statut En instance
Date de dépôt 2021-08-10
Date de disponibilité au public 2022-02-11
Propriétaire THE BOEING COMPANY (USA)
Inventeur(s)
  • Aaron, Noah Eric
  • Prewett, Emily M.

Abrégé

A method includes obtaining a first test matrix for a first aircraft system and a second test matrix for a second aircraft system. The method also includes, during a first operational test of the first test matrix, obtaining sensor data that includes second sensor data that is not specified by the first test matrix. The method includes evaluating a second operational test of the second test matrix by processing the second sensor data using a second analytic model of the second aircraft system. The method also includes generating second predicted sensor data based on the evaluation of the second operational test. The method includes generating a second error measure by comparing a second subset of the sensor data to the second predicted sensor data. The method includes determining, based at least in part on a range of the second sensor data, a test coverage metric of the second test matrix.

Classes IPC  ?

  • B64D 47/00 - Equipements non prévus ailleurs
  • B64F 5/60 - Test ou inspection des composants ou des systèmes d'aéronefs

31.

COLLISION AVOIDANCE BASED ON CENTRALIZED COORDINATION OF VEHICLE OPERATIONS

      
Numéro de document 03123068
Statut En instance
Date de dépôt 2021-06-22
Date de disponibilité au public 2022-02-07
Propriétaire THE BOEING COMPANY (USA)
Inventeur(s)
  • Hui, Leo Ho Chi
  • Krikorian, Haig Francis

Abrégé

A computer-implemented method performed by a centralized coordinated vehicle guidance system may include: obtaining analytics data for a plurality of vehicles or objects centrally communicating with or detected by the centralized coordinated vehicle guidance system; detecting, based on the analytics data, a collision event within one or more vehicle-object pairs; determining trajectory adjustment information for one or more vehicle in the vehicle-object pairs involved in the collision event; and outputting the trajectory adjustment information to cause the vehicle to modify its trajectory.

Classes IPC  ?

  • B60W 30/09 - Entreprenant une action automatiquement pour éviter la collision, p.ex. en freinant ou tournant
  • B60W 60/00 - Systèmes d’aide à la conduite spécialement adaptés aux véhicules routiers autonomes
  • G05D 1/02 - Commande de la position ou du cap par référence à un système à deux dimensions

32.

REAL TIME MULTIPLE AGENT ENGAGEMENT DECISION SYSTEM

      
Numéro de document 03123065
Statut En instance
Date de dépôt 2021-06-22
Date de disponibilité au public 2022-02-07
Propriétaire THE BOEING COMPANY (USA)
Inventeur(s)
  • Hui, Leo H.
  • Krikorian, Haig Francis

Abrégé

Agent/client pairs in at least one priority tier are determined. A matrix value is determined for each agent/client pair based on the client rank of the agent/client pair. An engagement capability parameter is determined for each agent/client pair. The matrix value for each disallowed agent/ranked client value is set to a zero value. All possible engagement options are evaluated. Candidate pair paths are determined by determining pair paths having a highest initial path value. The initial path value of each candidate pair path is decreased based on agent/client pairs in the candidate pair path that are urgent agent/client pairs or risky agent/client pairs to derive a final path value for each candidate pair path. A best path is determined based on the final path value for each candidate pair path. At least one engagement decision is derived based on the best path and transmitted towards agents in the best path.

Classes IPC  ?

  • G06Q 10/00 - Administration; Gestion
  • G06F 17/00 - TRAITEMENT ÉLECTRIQUE DE DONNÉES NUMÉRIQUES Équipement ou méthodes de traitement de données ou de calcul numérique, spécialement adaptés à des fonctions spécifiques

33.

WING ASSEMBLY HAVING WING JOINTS JOINING OUTER WING STRUCTURES TO CENTERWING STRUCTURE

      
Numéro de document 03120840
Statut En instance
Date de dépôt 2021-06-02
Date de disponibilité au public 2022-01-29
Propriétaire THE BOEING COMPANY (USA)
Inventeur(s)
  • Behzadpour, Forouzan
  • Stickler, Patrick B.

Abrégé

A wing assembly includes a center wing structure and a pair of outer wing structures. The center wing structure includes a center wing front spar, a center wing rear spar, and an engine mounting location on each side of a wing centerline. Each outer wing structure includes an outer wing front and rear spar configured to be coupled respectively to the center wing front and rear spar to define a wing joint coupling the outer wing structure to the center wing structure. The center wing structure is configured such that the spar terminal ends of the center wing front and rear spars at each wing joint are located no further inboard than an engine centerline associated with the engine mounting location, and no further outboard of the engine centerline than ten percent of a distance between the engine centerline and the wing centerline.

Classes IPC  ?

34.

BEAD-STIFFENED MOVABLE SURFACES

      
Numéro de document 03122789
Statut En instance
Date de dépôt 2021-06-16
Date de disponibilité au public 2022-01-29
Propriétaire THE BOEING COMPANY (USA)
Inventeur(s)
  • Behzadpour, Forouzan
  • Ashmawi, Waeil M.
  • Apdalhaliem, Sahrudine

Abrégé

A movable surface of an aircraft has a front spar extending along a spanwise direction between opposing movable surface ends. The movable surface also includes a plurality of ribs defining a plurality of bays between adjacent pairs of the ribs. Each rib extends between the front spar and a trailing edge portion of the movable surface. The movable surface further includes an upper and a lower skin panels coupled to the ribs and the front spar. In addition, the bull surface includes a plurality of bead stiffeners coupled to an inner surface of at least one of the upper skin panel and the lower skin panel. The bead stiffeners within the bays are spaced apart from each other and are oriented non-parallel to the front spar and have a bead stiffener cap having opposing cap ends respectively locate proximate the front spar and the trailing edge portion.

Classes IPC  ?

  • B64C 1/06 - Cadres; Lisses; Longerons
  • B64F 5/10 - Fabrication ou assemblage d’aéronefs, p.ex. gabarits à cet effet

35.

SYSTEMS AND METHODS FOR DETERMINING A STATE OF A STOWAGE BIN ASSEMBLY WITHIN AN INTERNAL CABIN OF A VEHICLE

      
Numéro de document 03122805
Statut En instance
Date de dépôt 2021-06-17
Date de disponibilité au public 2022-01-29
Propriétaire THE BOEING COMPANY (USA)
Inventeur(s)
  • Radhakrishnan, Venkatesh Babu
  • Rakesh, Mugaludi Ramesha
  • Savadamuthu, Madhanmohan
  • Tripathi, Shubham
  • Owyang, Ethan Carl

Abrégé

A system includes one or more components within an internal cabin of a vehicle. An imaging device is configured to obtain an image of the one or more components. A state determination control unit includes a processor. The state determination control unit is in communication with the imaging device. The state determination control unit receives image data including the image from the imaging device. Further, the state determination control unit determines a state of the one or more components based on the image data.

Classes IPC  ?

  • B60R 99/00 - Matière non prévue dans les autres groupes de la présente sous-classe

36.

COMPOSITE THIN WINGBOX ARCHITECTURE FOR SUPERSONIC BUSINESS JETS

      
Numéro de document 03124206
Statut En instance
Date de dépôt 2021-07-07
Date de disponibilité au public 2022-01-29
Propriétaire THE BOEING COMPANY (USA)
Inventeur(s)
  • Behzadpour, Forouzan
  • Stickler, Patrick B.

Abrégé

An apparatus including one or more panels including an outer face sheet comprising a plurality of first composite materials; an inner face sheet comprising a plurality of second composite materials; and a plurality of foam pieces disposed between the outer face sheet and the inner face sheet, wherein the foam pieces reduce warping of the panels.

Classes IPC  ?

  • B64C 3/26 - Construction, forme ou fixation des revêtements distincts, p.ex. panneaux
  • B64F 5/10 - Fabrication ou assemblage d’aéronefs, p.ex. gabarits à cet effet
  • B64C 3/00 - Voilures

37.

PROVIDING CONTINUOUSLY VARIABLE FEEL FORCES FOR FULLY-POWERED FLIGHT CONTROL SYSTEMS

      
Numéro de document 03121318
Statut En instance
Date de dépôt 2021-06-04
Date de disponibilité au public 2022-01-24
Propriétaire THE BOEING COMPANY (USA)
Inventeur(s) Elliot, Joseph E.

Abrégé

ABSTRACT In one or more embodiments, a method for providing continuously variable feel forces for an aircraft comprises sensing, by each of at least one sensor associated with at least one aircraft control, a force sensor value. The method further comprises determining a net force value by using the force sensor value for each of at least one sensor. Also, the method comprises comparing the net force value to a desired breakout force. In addition, the method comprises determining whether the net force value exceeds the desired breakout force. Additionally, the method comprises determining an adjusted force value by using the desired breakout force and the net force value, when the net force value exceeds the desired breakout force. Also, the method comprises determining an actuator torque command based on the adjusted force value. Further, the method comprises commanding an autopilot actuator with the actuator torque command to apply torque. Date Recue/Date Received 2021-06-04

Classes IPC  ?

  • B64C 13/00 - Systèmes de commande ou systèmes de transmission pour actionner les gouvernes, les volets hypersustentateurs, les aérofreins ou les destructeurs de portance (spoilers)
  • B64C 31/00 - Aéronefs prévus pour une sustentation sans moteur; Aéronefs du type pendulaire avec moteur de propulsion; Aéronefs du type ultra-léger
  • G05D 17/02 - Commande d'un couple; Commande de la puissance mécanique caractérisée par l'utilisation de moyens électriques

38.

LABYRINTH BARRIER WITH MEMBERS CONSTRUCTED OF A SHAPE MEMORY MATERIAL

      
Numéro de document 03118681
Statut En instance
Date de dépôt 2021-05-13
Date de disponibilité au public 2022-01-15
Propriétaire THE BOEING COMPANY (USA)
Inventeur(s)
  • Berkey, Tyler Emerson
  • Page, Nicholas

Abrégé

A labyrinth barrier is disclosed and comprises two or more members each defining respective vertical axes. One or more of the members are constructed at least in part of a shape memory material having a first energy state and a second energy state. The members are oriented relative to one another by their respective vertical axes in an original state to create a flow pathway that restricts fluid flow in a direction transverse to the respective vertical axes. The members are urged towards one another to further restrict the flow pathway when the shape memory material transitions from the first energy state to the second energy state.

Classes IPC  ?

  • F16J 15/447 - Garnitures à labyrinthe
  • F16J 15/453 - Garnitures à labyrinthe caractérisées par l'emploi de matériaux particuliers

39.

REPAIRING A SOLAR CELL BONDED ON A FLEXIBLE CIRCUIT

      
Numéro de document 03123147
Statut En instance
Date de dépôt 2021-06-23
Date de disponibilité au public 2022-01-15
Propriétaire THE BOEING COMPANY (USA)
Inventeur(s) Luc, Phil

Abrégé

A method of repairing a solar cell bonded on a substrate, by bonding a replacement solar cell on top of an existing solar cell, without removing the existing solar cell. The substrate may comprise a flexible circuit, printed circuit board, flex blanket, or solar cell panel. The bonding of the replacement solar cell on top of the existing solar cell uses a controlled adhesive pattern. Electrical connections for the existing solar cell and the replacement solar cell are made using electrical conductors on, above or embedded within the substrate. The electrical connections may extend underneath the replacement solar cell. The method further comprises removing interconnects for the electrical connections for the existing solar cell, and then welding or soldering interconnects for the electrical connections for the replacement solar cell.

Classes IPC  ?

  • H01L 31/18 - Procédés ou appareils spécialement adaptés à la fabrication ou au traitement de ces dispositifs ou de leurs parties constitutives
  • H01L 31/05 - Moyens d’interconnexion électrique entre les cellules PV à l’intérieur du module PV, p.ex. connexion en série de cellules PV

40.

FASTENING SYSTEM FOR AIRCRAFT STRUCTURES

      
Numéro de document 03123442
Statut En instance
Date de dépôt 2021-06-25
Date de disponibilité au public 2022-01-02
Propriétaire THE BOEING COMPANY (USA)
Inventeur(s)
  • Block, Samuel L.
  • Davies, John A.
  • Schroeder, Ian E.

Abrégé

A fastening system to couple a first aircraft structure and a second aircraft structure is disclosed. The fastening system includes a fastener, a nutplate having a body defining an opening to receive the fastener, a flange extending from the body to engage an outer surface of the first structure, and a first sleeve protruding from the flange in a direction away from the body, the first sleeve to couple to a first bore formed in the first structure and prevents rotation of the nutplate relative to the first structure.

Classes IPC  ?

  • F16B 5/02 - Jonction de feuilles ou de plaques soit entre elles soit à des bandes ou barres parallèles à elles par organes de fixation utilisant un filetage
  • B64F 5/10 - Fabrication ou assemblage d’aéronefs, p.ex. gabarits à cet effet
  • B64C 1/06 - Cadres; Lisses; Longerons
  • B64C 3/26 - Construction, forme ou fixation des revêtements distincts, p.ex. panneaux
  • F16B 37/04 - Dispositifs pour fixer les écrous à des surfaces, p.ex. à des feuilles, à des plaques

41.

QUANTUM PROCESSING SYSTEM

      
Numéro de document 03118674
Statut En instance
Date de dépôt 2021-05-13
Date de disponibilité au public 2021-12-17
Propriétaire THE BOEING COMPANY (USA)
Inventeur(s)
  • Thompson, Richard Joel
  • Kagele, Marna M.

Abrégé

A method, apparatus, system, and computer program product for quantum processing. A target quantum programming for a process for a quantum computer is identified. A universal gate set is selected based on a computer type. Any operation possible for a particular quantum computer can be performed using the universal gate set. Instructions for the process in a source quantum programming language are sent to a source quantum language translator which outputs a digital model representation of quantum computer components that are arranged to perform the process using the instructions. The digital model representation of the quantum computer components and the universal gate set are sent to a target quantum language translator, which outputs the instructions for operations for the process in a target quantum programming language using the digital model representation of the quantum computer components and the universal gate set for the computer type for the quantum computer.

Classes IPC  ?

  • G06N 10/20 - Modèles d’informatique quantique, p.ex. circuits quantiques ou ordinateurs quantiques universels

42.

OBJECT MONITORING SYSTEM FOR AIRCRAFT

      
Numéro de document 03117979
Statut En instance
Date de dépôt 2021-05-10
Date de disponibilité au public 2021-12-12
Propriétaire THE BOEING COMPANY (USA)
Inventeur(s)
  • Hunt, Jeffrey H.
  • Blake, Pamela L.

Abrégé

A method, apparatus, system, and computer program product for monitoring a platform. images are received by a computer system from a sensor system positioned to monitor movement of human beings relative to the platform. A set of the human beings is identified by the computer system in the images. The movement of the set of the human beings relative to the platform is determined by the computer system using the images. A count of the human beings on the platform is determined by the computer system based on the movement determined for the set of the human beings. A set of actions is performed by the computer system based on the count of the human beings on the platform.

Classes IPC  ?

  • G01D 21/00 - Mesures ou tests non prévus ailleurs
  • G06Q 50/30 - Transport; Communications
  • B64D 47/00 - Equipements non prévus ailleurs
  • B64F 1/00 - Installations au sol ou installations pour ponts d'envol des porte-avions
  • G01N 21/84 - Systèmes spécialement adaptés à des applications particulières
  • G01N 22/00 - Recherche ou analyse des matériaux par l'utilisation de micro-ondes ou d'ondes radio, c. à d. d'ondes électromagnétiques d'une longueur d'onde d'un millimètre ou plus
  • G01N 23/00 - 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
  • G01S 17/89 - Systèmes lidar, spécialement adaptés pour des applications spécifiques pour la cartographie ou l'imagerie

43.

MONUMENT HAVING ATTACHMENT SYSTEM WITH CORNER BRACKET FITTING

      
Numéro de document 03116973
Statut En instance
Date de dépôt 2021-04-30
Date de disponibilité au public 2021-12-12
Propriétaire THE BOEING COMPANY (USA)
Inventeur(s)
  • Young, Stephen M.
  • Ramirez, Saul
  • Baek, Joshua Youngmin

Abrégé

A monument is presented. The monument comprises a floor panel; a left face panel perpendicular to the floor panel; a right face panel perpendicular to the floor panel; and an attachment system connecting the floor panel, the left face panel, and the right face panel. The attachment system comprises a right corner bracket fitting connecting the right face panel to the floor panel; a left corner bracket fitting connecting the left face panel to the floor panel; and a filler panel connected to and extending between the right corner bracket fitting and the left corner bracket fitting.

Classes IPC  ?

44.

MULTILEVEL COMBINATIONAL OPTIMIZER FOR RESOURCE PLANNING

      
Numéro de document 03112668
Statut En instance
Date de dépôt 2021-03-19
Date de disponibilité au public 2021-12-10
Propriétaire THE BOEING COMPANY (USA)
Inventeur(s)
  • Svynaryov, Andriy
  • Bjork, Magnus
  • Pietrzak, Pawel

Abrégé

The present disclosure provides a multilevel combinatorial optimizer for resource planning that identifies resource use preferences for a set of resources and a set of tasks to be performed; assigns resources to tasks to generate a strict-priority assignment set; in response to reaching a process break: identifies a subset of resources below a specified priority level; assigns the subset to unassigned tasks until each task is fully assigned to provide a full-assignment assignment set; in response to completing assignments for the set of tasks: rectifying inversions in the full-assignment assignment set by: selecting a tuple size for swapping the resources among tasks; identifying tuples of assignments that include an inversion; swapping the assignments identified in the tuples to remove the inversion and update the full-assignment assignment set to a reduced-inversion assignment set; and in response to the reduced-inversion assignment set including no inversions, outputting the reduced-inversion assignment set.

Classes IPC  ?

  • G06Q 10/06 - Ressources, gestion de tâches, gestion d'hommes ou de projets, p.ex. organisation, planification, ordonnancement ou affectation de ressources en temps, hommes ou machines; Planification dans l'entreprise; Modèles organisationnels

45.

COMPOSITE DOORS AND METHODS OF FORMING THEREOF

      
Numéro de document 03116053
Statut En instance
Date de dépôt 2021-04-23
Date de disponibilité au public 2021-12-10
Propriétaire THE BOEING COMPANY (USA)
Inventeur(s)
  • Walker, Steven P.
  • Martinez, Perlas G.

Abrégé

A composite door (100) comprises a composite frame (110), which comprises a first rail (111), a second rail (112), and crossbeams (113), joining the first rail (111) and the second rail (112). The composite door (100) also comprises a first composite side beam (130), a second composite side beam (140), and a composite skin (150), connected to each of the crossbeams (113) of the composite frame (110), to the first composite side beam (130), and to the second composite side beam (140). The composite door (100) further comprises first composite edge fittings (120), each connected to a corresponding one of the crossbeams (113) of the composite frame (110), to the first composite side beam (130), and to the composite skin (150), and second composite edge fittings (122), each connected to a corresponding one of the crossbeams (113) of the composite frame (110), to the second composite side beam (140), and to the composite skin (150).

Classes IPC  ?

  • B64C 1/14 - Fenêtres; Portes; Trappes d'évacuation ou panneaux de visite; Structures de cadres environnants; Verrières; Pare-brise
  • B64F 5/10 - Fabrication ou assemblage d’aéronefs, p.ex. gabarits à cet effet
  • 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 noyau; Façonnage par pistolage, c.à d. pulvérisation de fibres sur un moule, un gabarit ou un noyau
  • E06B 3/70 - Vantaux de porte

46.

LOCKING PANEL ASSEMBLY

      
Numéro de document 03111195
Statut En instance
Date de dépôt 2021-03-04
Date de disponibilité au public 2021-12-09
Propriétaire THE BOEING COMPANY (USA)
Inventeur(s)
  • Osborne, John C.
  • Scott, Steven A.

Abrégé

A panel assembly for installation onto a track beam including a beam flange having a non- linear edge is disclosed. The panel assembly includes a panel and a lockable catch moveably connected to the panel. The lockable catch includes a lockable mating edge configured to selectively mate with the non-linear edge of the beam flange of the track beam. The lockable catch also includes a lockable catch edge extending beyond the lockable mating edge. The lockable catch is moveable on a lower surface of the panel between an unlocked position and a locked position. In the unlocked position the lockable catch edge is retracted. In the locked position, the lockable mating edge mates with the non-linear edge of the beam flange and the lockable catch edge retains the panel on the track beam.

Classes IPC  ?

  • B64C 1/18 - Planchers
  • E04F 15/00 - Revêtements de sols
  • F16B 5/00 - Jonction de feuilles ou de plaques soit entre elles soit à des bandes ou barres parallèles à elles

47.

PASSENGER DOOR LOCK FOR DROP-DOWN STYLE DOORS ON AN AIRCRAFT

      
Numéro de document 03116058
Statut En instance
Date de dépôt 2021-04-23
Date de disponibilité au public 2021-12-09
Propriétaire THE BOEING COMPANY (USA)
Inventeur(s) Hummer, David A.

Abrégé

Apparatus, systems, and methods for selectively locking and unlocking a passenger door. The apparatus includes a first shaft (110) having a first longitudinal centerline (111) and a member (120) connected to the first shaft (110). A handle (130) is connected to the first shaft (110) via the member (120), the handle (130) being movable via rotation of the first shaft (110) from a locked position and an unlocked position. A first protrusion (140, 140A) extends from the handle (130) and a latch crank (160) is connected to the second shaft (150). A second protrusion (170, 170A) extends from the latch crank (160) and a linkage (180) is connected between the latch crank (160) and the member (120). When the handle (130) in the locked position, the first protrusion (140, 140A) is positioned adjacent to the second protrusion (170, 170A) to prevent rotation of the second shaft (150). When the handle (130) is in the unlocked position, the first protrusion (140, 140A) is positioned away from the second protrusion (170, 170A) to enable the second shaft (150) to rotate.

Classes IPC  ?

  • E05B 77/32 - Serrures de véhicule caractérisées par des fonctions ou des fins particulières permettant l’actionnement simultané d’éléments de verrouillage ou de déverrouillage et d’une poignée, p.ex. pour empêcher l'interférence entre une action de déverrouillage et une action de déclenchement
  • E05B 63/00 - Serrures à caractéristiques structurales particulières

48.

DYNAMIC LOAD DAMPING APPARATUS

      
Numéro de document 03114086
Statut En instance
Date de dépôt 2021-04-06
Date de disponibilité au public 2021-12-05
Propriétaire THE BOEING COMPANY (USA)
Inventeur(s) Christenson, Justin

Abrégé

A dynamic load damping apparatus is employed in a hydraulic steering system control circuit of an aircraft. The dynamic load damping apparatus is positioned in the hydraulic steering system control circuit in parallel with a control valve of the control circuit that functions as the hydraulic fluid source of the control circuit and an actuator that controls movements of a nose gear of the aircraft. The dynamic load damping apparatus dampens loads transmitted to the hydraulic actuator that controls the steering movements of the nose gear on the aircraft.

Classes IPC  ?

  • F16F 9/34 - Structure des clapets particuliers; Forme ou structure des passages d'étranglement
  • B64C 25/50 - Atterrisseurs orientables; Amortissement du shimmy
  • F15C 3/02 - Eléments de circuits ayant des parties en mouvement utilisant des clapets à bobines

49.

VARIABLE FLUID DAMPING

      
Numéro de document 03116057
Statut En instance
Date de dépôt 2021-04-23
Date de disponibilité au public 2021-12-04
Propriétaire THE BOEING COMPANY (USA)
Inventeur(s)
  • Nyamagoudar, Vinayak M.
  • Chandar N C, Aswin

Abrégé

Disclosed herein is an apparatus for variable fluid damping. The apparatus comprises a mount. The apparatus also comprises a damper coupled to the mount to apply a damping force in response to movement of the mount. The apparatus further comprises an electrical element positioned to correspond to the damper. The apparatus additionally comprises a rheological fluid disposed in the damper. The rheological fluid changes viscosity in response to a change in an output of the electrical element to change the damping force of the damper. The apparatus also comprises a controller to provide input to the electrical element in response to a normal operating condition or an emergency operating condition.

Classes IPC  ?

  • F16F 9/53 - Moyens pour le réglage des caractéristiques des amortisseurs en faisant varier la viscosité du fluide, p.ex. électromagnétiques
  • B60J 5/00 - Portes
  • E05F 3/14 - Appareils de fermeture ou d'ouverture à dispositif de freinage, p.ex. ralentisseurs; Structure des dispositifs de freinage pneumatique ou à liquide à freins à fluide du type rotatif
  • F16F 9/46 - Ressorts, amortisseurs de vibrations, amortisseurs de chocs ou amortisseurs de mouvement de structure similaire, utilisant un fluide ou moyen équivalent comme agent d'amortissement - Parties constitutives de tels dispositifs combinés avec la correction de température permettant la commande à distance

50.

SYSTEMS AND METHODS FOR DEPOSITION AND HIGH-FREQUENCY MICROWAVE INSPECTION OF UNCURED FIBER-REINFORCED POLYMERIC MATERIALS

      
Numéro de document 03116970
Statut En instance
Date de dépôt 2021-04-30
Date de disponibilité au public 2021-12-03
Propriétaire THE BOEING COMPANY (USA)
Inventeur(s)
  • Safai, Morteza
  • Georgeson, Gary E.

Abrégé

Disclosed herein is a system that comprises a deposition head configured to deposit multiple tows in a stacked configuration one layer at a time. Each tow of the multiple tows is a currently-applied tow when the tow is a most-recently deposited tow of the multiple tows and a tow of the multiple tows is a covered tow when the tow is directly covered by the currently-applied tow. The system also comprises a probe head, configured to move along and be spatially offset from the currently-applied tow after deposition of the currently-applied tow. The probe head is further configured to transmit an incident microwave beam into the currently-applied tow as the probe head moves along the currently-applied tow. The incident microwave beam has a frequency low enough to pass entirely through the currently-applied tow and high enough to pass entirely through no more than the currently-applied tow and the covered tow.

Classes IPC  ?

  • B29C 64/194 - Procédés de fabrication additive impliquant des opérations supplémentaires effectuées sur les couches ajoutées, p.ex. lissage, meulage ou contrôle d’épaisseur pendant l’empilage des couches
  • B33Y 10/00 - Procédés de fabrication additive
  • B33Y 30/00 - Appareils pour la fabrication additive; Leurs parties constitutives ou accessoires à cet effet
  • B33Y 50/00 - Acquisition ou traitement de données pour la fabrication additive
  • B29C 64/379 - Manutention des objets en 3D obtenus, p.ex. à l’aide de robots
  • 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 noyau; Façonnage par pistolage, c.à d. pulvérisation de fibres sur un moule, un gabarit ou un noyau
  • G01S 13/88 - Radar ou systèmes analogues, spécialement adaptés pour des applications spécifiques
  • G01B 11/00 - Dispositions pour la mesure caractérisées par l'utilisation de moyens optiques

51.

AIRCRAFT WITH MULTI SPAR BOX CONNECTION TO FUSELAGE

      
Numéro de document 03110697
Statut En instance
Date de dépôt 2021-02-26
Date de disponibilité au public 2021-11-27
Propriétaire THE BOEING COMPANY (USA)
Inventeur(s)
  • Ryder, Kevin P.
  • Coates, Charles R.
  • Newnham, Peter J.
  • Pearson, William H.
  • Campana, Joseph H.

Abrégé

An aircraft has a vertical stabilizer with a multi-spar box and a base rib assembly secured to the multi-spar box. The base rib assembly has front longitudinal lugs, rear longitudinal lugs, and opposing middle longitudinal lugs. Front clevises corresponding to the front longitudinal lugs are secured to frame members of the fuselage of the aircraft and each has a first, second, and third mounting arms. Rear clevises corresponding to the rear longitudinal lugs are secured to frame members and each has a first, second, and third mounting arms. Middle clevises corresponding to the middle longitudinal lugs are secured to frame members and each has only first and second mounting arms. Retaining members inserted through mounting holes in each longitudinal lug and mounting holes in each corresponding clevis secures the vertical stabilizer to the fuselage.

Classes IPC  ?

  • B64C 1/26 - Fixation de la voilure, des empennages ou des surfaces stabilisatrices

52.

APPARATUS, SYSTEMS, AND METHODS FOR FORMING ALIGNED HOLES FROM MISALIGNED HOLES

      
Numéro de document 03113192
Statut En instance
Date de dépôt 2021-03-24
Date de disponibilité au public 2021-11-27
Propriétaire THE BOEING COMPANY (USA)
Inventeur(s)
  • Ward, Michael A.
  • Scheibel, John P.
  • Scherer, James L.

Abrégé

Apparatus, systems, and methods for forming a plurality of aligned holes from a plurality of misaligned holes. The apparatus includes a reamer with a constant diameter a first portion and a tapered second portion. A constant diameter pilot member is connected to the reamer. The taper may be configured to center the reamer and reduce an offset between the apparatus and a centerline of a virtual hole created by the misaligned holes. The constant diameter of the pilot member corresponds to the virtual hole and the constant diameter of the first portion of the reamer correspond to a cleanup hole configured to accept an oversize fastener and fully encompass the misaligned holes. If the pilot member cannot pass through the misaligned holes, an apparatus with a smaller diameter pilot member and a larger diameter reamer is needed to create a cleanup hole that fully encompasses the misaligned holes.

Classes IPC  ?

  • B23B 51/00 - Outils pour machines à percer
  • B23B 49/00 - Systèmes de mesure ou de calibrage des machines à aléser, pour le positionnement ou le guidage du foret; Dispositif pour indiquer les défauts des forets pendant l'alésage; Dispositifs à centrer les trous à aléser

53.

STRUCTURAL COMPOSITE AIRFOILS WITH DIRECTLY COUPLED FRONT SPARS, AND RELATED METHODS

      
Numéro de document 03111198
Statut En instance
Date de dépôt 2021-03-04
Date de disponibilité au public 2021-11-21
Propriétaire THE BOEING COMPANY (USA)
Inventeur(s)
  • Gruner, Bryan
  • Schupp, Peter

Abrégé

Structural composite airfoils include a primary structural element, a secondary structural element defining the trailing edge of the structural composite airfoil, and a leading edge skin panel defining the leading edge of the structural composite airfoil. The primary structural element includes an upper skin panel, a lower skin panel, and a front C-channel spar. A first channel of the front C- channel spar faces the leading edge of the structural composite airfoil, and an upper flange of the front C-channel spar forms an acute angle with an elongated span of the front C-channel spar. The leading edge skin panel is positioned adjacent the leading edge region of the primary structural element, with a first end region of the leading edge skin panel being coupled to the upper flange of the front C-channel spar, and a second end region being coupled to the lower flange of the front C- channel spar.

Classes IPC  ?

54.

NOSE LANDING GEAR ASSEMBLY FOR USE WITH AN AIRCRAFT

      
Numéro de document 03113323
Statut En instance
Date de dépôt 2021-03-25
Date de disponibilité au public 2021-11-21
Propriétaire THE BOEING COMPANY (USA)
Inventeur(s)
  • Karapetian, Michael S.
  • Lee, Hao

Abrégé

A nose landing gear assembly includes an oleo strut, a forward brace including a forward brace first end and a forward brace second end. The forward brace first end is pivotably coupled to the nose gear bay of a high wing aircraft about a first pivot axis. The assembly also includes an aft brace including an aft brace first end and an aft brace second end. The aft brace first end is pivotably coupled to the nose gear bay about a second pivot axis, and the aft brace second end is pivotably coupled to the oleo strut. An actuator includes an actuator first end and an actuator second end. The actuator second end is coupled to the nose gear bay and the actuator first end coupled to the forward brace. The actuator is configured to move the nose landing gear assembly between a retracted position and an extended position.

Classes IPC  ?

  • B64C 25/18 - Mécanismes de manœuvre
  • B64C 25/14 - Atterrisseurs non fixes, p.ex. largables escamotables, repliables ou ayant un mouvement apparenté d'avant en arrière

55.

PORTABLE SANITIZING SYSTEMS AND METHODS WITH RANGE GUIDANCE

      
Numéro de document 03119128
Statut En instance
Date de dépôt 2021-05-19
Date de disponibilité au public 2021-11-20
Propriétaire THE BOEING COMPANY (USA)
Inventeur(s) Childress, Jamie J.

Abrégé

A sanitizing head includes a housing and multiple range light sources. The housing retains an ultraviolet (UV) lamp, and UV light emitted from the UV lamp exits through a front end of the housing. The range light sources are secured to the housing and arranged in one or more pairs. The range light sources in each pair of the one or more pairs are oriented relative to each other to emit respective light beams that converge at a predetermined distance in front of the UV lamp.

Classes IPC  ?

  • A61L 2/10 - Procédés ou appareils de désinfection ou de stérilisation de matériaux ou d'objets autres que les denrées alimentaires ou les lentilles de contact; Accessoires à cet effet utilisant des phénomènes physiques des radiations des ultraviolets

56.

BEAM STEERING FOR LASER ULTRASONIC INSPECTION SYSTEMS

      
Numéro de document 03112162
Statut En instance
Date de dépôt 2021-03-12
Date de disponibilité au public 2021-11-20
Propriétaire THE BOEING COMPANY (USA)
Inventeur(s) Safai, Morteza

Abrégé

Disclosed herein is a laser ultrasonic testing (UT) apparatus for inspecting a surface of an object. The laser UT apparatus comprises an excitation laser, which is selectively operable to generate an excitation laser beam. The laser UT apparatus also comprises a first acousto-optic deflector (AOD) and a second AOD. The laser UT apparatus additionally comprises a detection laser, which is selectively operable to generate a detection laser beam. The laser UT apparatus further comprises a third AOD and a fourth AOD.

Classes IPC  ?

  • G01N 29/14 - Recherche ou analyse des matériaux par l'emploi d'ondes ultrasonores, sonores ou infrasonores; Visualisation de l'intérieur d'objets par transmission d'ondes ultrasonores ou sonores à travers l'objet utilisant des techniques d'émission acoustique
  • G01B 17/06 - Dispositions pour la mesure caractérisées par l'utilisation de vibrations infrasonores, sonores ou ultrasonores pour mesurer des contours ou des courbes
  • G01N 29/265 - Dispositions pour l'orientation ou le balayage en déplaçant le capteur par rapport à un matériau fixe

57.

ADDITIVELY MANUFACTURED SATELLITE

      
Numéro de document 03108461
Statut En instance
Date de dépôt 2021-02-05
Date de disponibilité au public 2021-11-18
Propriétaire THE BOEING COMPANY (USA)
Inventeur(s)
  • Aston, Richard W.
  • Joe, Christopher David
  • Hastings, Nicole Marie
  • Schoeborn, Nicole Diane
  • Zilz, Rachel Elizabeth
  • Sharma, Arjun

Abrégé

A satellite is disclosed, including a body and a communication device attached to the body. The body has an additively manufactured external wall structure at least partially forming an enclosed compartment, and the communication device is configured to receive and transmit data while in space.

Classes IPC  ?

  • B64G 1/10 - Satellites artificiels; Systèmes de tels satellites; Véhicules interplanétaires
  • B33Y 10/00 - Procédés de fabrication additive
  • B33Y 80/00 - Produits obtenus par fabrication additive

58.

THERMAL CONTROL SYSTEMS FOR AIRCRAFT LANDING GEAR WHEEL WELLS AND RELATED METHODS

      
Numéro de document 03113412
Statut En instance
Date de dépôt 2021-03-26
Date de disponibilité au public 2021-11-15
Propriétaire THE BOEING COMPANY (USA)
Inventeur(s)
  • Clark, Andrew David
  • Al-Alusi, Thamir Rauf
  • Kirkbride, David William
  • Calkins, Frederick T.
  • Mitchell, Bradley J.

Abrégé

Thermal control system for aircraft main landing gear wheel wells and related methods are disclosed. An example thermal control system includes a conduit defining a fluid passageway between an inlet and an outlet. The inlet of the conduit positioned in fluid communication with a landing gear wheel well and the outlet of the conduit positioned in fluid communication with the atmosphere. The conduit generates a pressure differential through the fluid passageway between the inlet and the outlet to exhaust heat from the landing gear wheel well to the atmosphere.

Classes IPC  ?

  • B64D 13/00 - Aménagements ou adaptations des appareils de conditionnement d'air pour équipages d'aéronefs, passagers ou pour emplacement réservé au fret
  • B64C 25/00 - Trains d'atterrissage

59.

FABRICATING A SILICON CARBIDE AND NITRIDE STRUCTURES ON A CARRIER SUBSTRATE

      
Numéro de document 03113032
Statut En instance
Date de dépôt 2021-03-22
Date de disponibilité au public 2021-11-14
Propriétaire THE BOEING COMPANY (USA)
Inventeur(s)
  • Whiteley, Samuel J.
  • Yap, Daniel
  • Chen, Edward H.
  • Kim, Danny M.
  • Ladd, Thaddeus D.

Abrégé

A method, apparatus, and system for forming a semiconductor structure. A first oxide layer located on a set of group III nitride layers formed on a silicon carbide substrate is bonded to a second oxide layer located on a carrier substrate to form an oxide layer located between the carrier substrate and the set of group III nitride layers. The silicon carbide substrate has a doped layer. The silicon carbide substrate having the doped layer is etched using a photo-electrochemical etching process, wherein a doping level of the doped layer is such that the doped layer is removed and a silicon carbide layer in the silicon carbide substrate remains unetched. The semiconductor structure is formed using the silicon carbide layer and the set of group III nitride layers.

Classes IPC  ?

  • H01L 21/00 - Procédés ou appareils spécialement adaptés à la fabrication ou au traitement de dispositifs à semi-conducteurs ou de dispositifs à l'état solide, ou bien de leurs parties constitutives
  • H01L 29/16 - Corps semi-conducteurs caractérisés par les matériaux dont ils sont constitués comprenant, mis à part les matériaux de dopage ou autres impuretés, seulement des éléments du groupe IV de la classification périodique, sous forme non combinée
  • H01L 29/20 - Corps semi-conducteurs caractérisés par les matériaux dont ils sont constitués comprenant, à part les matériaux de dopage ou autres impuretés, uniquement des composés AIIIBV

60.

SLIDING JOINT FOR LOAD ALLEVIATION

      
Numéro de document 03111917
Statut En instance
Date de dépôt 2021-03-11
Date de disponibilité au public 2021-11-10
Propriétaire THE BOEING COMPANY (USA)
Inventeur(s) Herter, Andrew J.

Abrégé

Example methods and systems for isolating and alleviating load in an aircraft are described, comprising providing a sliding joint between a seat track and a flight deck floor panel. The sliding joint comprises a lug comprising a first end and a second end opposite the first end, wherein the first end is adapted to attach to the seat track and the second end comprises an elongate aperture, and a clevis comprising an oblate shaped slider bushing that is coupled to the lug.

Classes IPC  ?

  • B64C 1/00 - Fuselages; Caractéristiques structurales communes aux fuselages, voilures, surfaces stabilisatrices ou organes apparentés
  • B64C 1/18 - Planchers
  • B64D 11/06 - Aménagements ou adaptations des sièges
  • F16B 7/00 - Assemblages de barres ou assemblages de tubes, p.ex. de section non circulaire, y compris les assemblages élastiques

61.

APPARATUSES, SYSTEMS, AND METHODS FOR DETECTING KISSING BONDS IN BONDED JOINTS

      
Numéro de document 03109682
Statut En instance
Date de dépôt 2021-02-19
Date de disponibilité au public 2021-11-01
Propriétaire THE BOEING COMPANY (USA)
Inventeur(s) Ashrafi, Mahdi

Abrégé

Disclosed herein is a detection assembly for detecting kissing bonds in a bonded joint of a part. The detection assembly comprises an electromagnetic shockwave generator that is configured to generate an electromagnetic shockwave through a target portion of the bonded joint. The electromagnetic shockwave has an intensity sufficient to induce a separation of a kissing bond in the target portion of the bonded joint and insufficient to induce a separation of a healthy bond, adjacent the kissing bond, in the target portion. The detection assembly also comprises an ultrasonic sensor that is configured to generate a transmitted ultrasonic pulse, direct the transmitted ultrasonic pulse into the target portion of the bonded joint, and receive a received ultrasonic pulse from the target portion of the bonded joint in response to the electromagnetic shockwave generator generating the electromagnetic shockwave through the target portion of the bonded joint.

Classes IPC  ?

  • G01N 29/04 - Analyse de solides
  • G01S 15/88 - Systèmes sonar, spécialement adaptés à des applications spécifiques

62.

TOOLS AND METHODS FOR FORMING ALIGNED HOLES FROM NEAR FULL-SIZED HOLES

      
Numéro de document 03111202
Statut En instance
Date de dépôt 2021-03-04
Date de disponibilité au public 2021-10-30
Propriétaire THE BOEING COMPANY (USA)
Inventeur(s)
  • Scheibel, John P.
  • Scherer, James L.
  • Ward, Michael A.

Abrégé

Tools and methods for creating a plurality of aligned holes from a plurality of near full-sized holes. The tool includes a cutting member having a first diameter and a pilot member connected to and coaxial with the cutting member. A first section of the pilot member includes a centering member and is positioned between the cutting member and the second section having a second diameter. The centering member may include a cutting surface. The second diameter corresponds to a positional tolerance of misalignment of a plurality of near full-sized holes of the same diameter and a full-size hole diameter. The centering member may have a third diameter between the first and second diameters. The centering member may be tapered. The pilot member may be inserted into a plurality of near-full sized holes and the cutting member may cut through the holes to form a plurality of aligned full sized holes.

Classes IPC  ?

  • B23B 51/00 - Outils pour machines à percer
  • B23B 49/00 - Systèmes de mesure ou de calibrage des machines à aléser, pour le positionnement ou le guidage du foret; Dispositif pour indiquer les défauts des forets pendant l'alésage; Dispositifs à centrer les trous à aléser

63.

AIRCRAFT INKJET PRINTING

      
Numéro de document 03112360
Statut En instance
Date de dépôt 2021-03-16
Date de disponibilité au public 2021-10-22
Propriétaire THE BOEING COMPANY (USA)
Inventeur(s)
  • Yaghoobi, Ahmad R.
  • Mellin, Matthew H.
  • Greene, Edward R.
  • Larson-Smith, Kjersta L.
  • Ahmady, Temourshah
  • Srinivasmurthy, Krishna P.

Abrégé

A method, apparatus, system, and computer program product for applying a color to an aircraft. The color for an exterior surface of the aircraft is determined by the computer system from a design of the aircraft. A position of the color in three-dimensional space is determined by the computer system. The position is in a color space coordinate system. An inkjet printer in the inkjet printers with a point cloud in the plurality of point clouds having a smallest Euclidean distance to the position of the color is selected by the computer system. The inkjet printer is used to apply the color on the exterior surface of the aircraft.

Classes IPC  ?

  • B64F 5/00 - Tracé, fabrication, assemblage, nettoyage, entretien ou réparation des aéronefs, non prévus ailleurs; Manipulation, transport, test ou inspection de composants d’aéronefs, non prévus ailleurs
  • B05D 5/06 - Procédés pour appliquer des liquides ou d'autres matériaux fluides aux surfaces pour obtenir des effets, finis ou des structures de surface particuliers pour obtenir des effets multicolores ou d'autres effets optiques
  • B41J 3/00 - Machines à écrire ou mécanismes d'impression ou de marquage sélectif caractérises par le but dans lequel ils sont construits

64.

MAGNETIC FIELD VISUALIZATION USING MODULATION SCREEN AND COMPRESSIVE SENSING

      
Numéro de document 03114842
Statut En instance
Date de dépôt 2021-04-13
Date de disponibilité au public 2021-10-20
Propriétaire THE BOEING COMPANY (USA)
Inventeur(s)
  • Tanielian, Minas H.
  • Daczko, Mateus S.
  • Martin, Lindsay
  • Adams, Alec
  • Goodbody, Carlene

Abrégé

Systems and methods for providing a visualization capability to map magnetic fields. The system utilizes a high-sensitivity magnetic field sensor (6) (e.g., a magnetometer (12) inside a tube (16) made of magnetic shielding material) disposed on one side of a magnetic field modulation screen (2) to acquire measurement data representing an image of a magnetic field. The magnetic field modulation screen includes a multiplicity of magnetic field-generating pixel elements (34) (e.g., current-carrying loops (20) made of electrically conductive material). Optionally, the system also uses compressive sensing techniques to reduce the amount of measurement data required to reconstruct an image of the original magnetic field. Compressive sensing is enabled by not supplying current to a different selected individual magnetic field-generating pixel element of the magnetic field modulation screen at successive sampling times.

Classes IPC  ?

  • G01R 33/10 - Tracé par points de la répartition de champ
  • G01R 33/02 - Mesure de la direction ou de l'intensité de champs magnétiques ou de flux magnétiques
  • H01F 5/00 - Bobines d'induction

65.

SYSTEMS AND METHODS FOR CONSTRUCTING A BONDED STRUCTURE

      
Numéro de document 03112150
Statut En instance
Date de dépôt 2021-03-12
Date de disponibilité au public 2021-10-08
Propriétaire THE BOEING COMPANY (USA)
Inventeur(s)
  • Hafenrichter, Joseph L.
  • Georgeson, Gary E.
  • Piehl, Marc J.

Abrégé

A bonded structure is described. The bonded structure includes an outer structure including a close tolerance hole associated with a first accuracy level. The bonded structure includes an interior structure comprising an oversized hole associated with a second accuracy level that is different from the first accuracy level. The bonded structure includes an elastomeric grommet disposed in the oversized hole. The bonded structure includes one or more spacers between the outer structure and the interior structure providing a space between the outer structure and the interior structure. The bonded structure includes a fastener positioned in the close tolerance hole and in the oversized hole. The bonded structure includes a bonding media disposed in the space between the outer structure and the interior structure via one or more channels of the fastener. The bonding media, elastomeric grommet, and oversized hole collectively position the interior structure relative to the outer structure.

Classes IPC  ?

  • B29C 65/48 - Assemblage d'éléments préformés; Appareils à cet effet en utilisant des adhésifs

66.

AIRCRAFT PRESSURE DECK

      
Numéro de document 03107251
Statut En instance
Date de dépôt 2021-01-26
Date de disponibilité au public 2021-10-07
Propriétaire THE BOEING COMPANY (USA)
Inventeur(s)
  • Leibov, David H.
  • Ingham, Steven D.
  • Cox, Daniel
  • Mclaughlin, Mark R.
  • Menanno, Alfons
  • Paravata, Soma Gopala
  • Sullivan, Kevin L.

Abrégé

Embodiments for aircraft pressure deck. One embodiment is a pressure deck of an aircraft. The pressure deck includes beams extending longitudinally along a fuselage of the aircraft, and a web attached to an underside of the beams, the web including arches between adjacent beams to allow the pressure deck to flex laterally. The pressure deck also includes a box structure between a middle pair of the beams and configured to transfer load forward to a rear spar of a wing of the aircraft and aft to an aft wheel well bulkhead of the aircraft. The pressure deck further includes a first intercostal outboard from the box structure and configured to stabilize a first outboard pair of the beams, and a second intercostal outboard from the first intercostal and coupled between a second outboard pair of the beams via a swing link to allow the second intercostal to flex laterally.

Classes IPC  ?

  • B64C 1/00 - Fuselages; Caractéristiques structurales communes aux fuselages, voilures, surfaces stabilisatrices ou organes apparentés
  • B64C 1/18 - Planchers

67.

DOUBLE TRANSLATING PLUG-TYPE PASSENGER ENTRY DOOR

      
Numéro de document 03112160
Statut En instance
Date de dépôt 2021-03-12
Date de disponibilité au public 2021-10-07
Propriétaire THE BOEING COMPANY (USA)
Inventeur(s) Beezhold, Benjamin Lee

Abrégé

The present disclosure provides an aircraft door system including an aircraft door configured to translate from a closed position to an open position. The aircraft door system further includes a plurality of door pressure stops positioned along a length of the aircraft door and a handle coupled to the aircraft door. A rotation of the handle causes a first translation of the aircraft door in an inward direction and a forward direction. The aircraft door system further includes a hinge system coupled to the aircraft door. An outward force applied to the aircraft door causes a second translation of the aircraft door in an outward direction and a forward direction. The hinge system causes the aircraft door to translate such that the aircraft door remains parallel to the aircraft fuselage throughout an entirety of the second translation until the aircraft door reaches the open position.

Classes IPC  ?

  • B64C 1/14 - Fenêtres; Portes; Trappes d'évacuation ou panneaux de visite; Structures de cadres environnants; Verrières; Pare-brise

68.

RECIRCULATING BALL SCREW ROTARY ACTUATOR

      
Numéro de document 03106791
Statut En instance
Date de dépôt 2021-01-21
Date de disponibilité au public 2021-10-01
Propriétaire THE BOEING COMPANY (USA)
Inventeur(s) Mellor, Mitchell

Abrégé

A rotary actuator for a hinged panel assembly, e.g., of a fixed-wing aircraft, includes ball bearings, an outer cylinder, a piston, and an inner shaft. The outer cylinder admits fluid pressure from a fluid pressure supply. The piston is circumscribed by the outer cylinder. The piston, outer cylinder, and ball bearings collectively forming an outer ball screw. The piston translates along a longitudinal center axis in response to the fluid pressure. The inner shaft is circumscribed by the piston, with the inner shaft, piston, and ball bearings collectively forming an inner ball screw that is concentric with the outer ball screw. The ball screws form an interlaced ball circuit with one or more shared ball paths. Piston translation rotates the piston and inner shaft, and to thereby recirculates the ball bearings between the outer ball screw and the inner ball screw through the interlaced ball circuit.

Classes IPC  ?

  • F16H 25/22 - Mécanismes à vis avec billes, rouleaux ou organes similaires entre pièces travaillant en conjugaison; Eléments essentiels pour l'utilisation de ces organes
  • B64C 13/40 - Dispositifs de transmission avec amplification de puissance utilisant la pression d'un fluide
  • F15B 15/06 - Schéma mécanique de montage caractérisé par les moyens transformant le mouvement de l'élément entraîné par le fluide en mouvement de l'organe terminal qui est actionné pour la transformation mécanique d'un mouvement rectiligne en un mouvement non rectiligne
  • F16H 25/12 - Transmissions comportant essentiellement et uniquement des systèmes came et galet ou des mécanismes à vis et écrous pour convertir un mouvement rotatif en mouvement alternatif et vice versa avec mouvement alternatif selon l'axe de rotation, p.ex. transmissions à gorges hélicoïdales et inversion automatique

69.

SCARF REPAIR APPARATUS, SYSTEM, AND METHOD

      
Numéro de document 03118224
Statut En instance
Date de dépôt 2021-05-12
Date de disponibilité au public 2021-09-26
Propriétaire THE BOEING COMPANY (USA)
Inventeur(s)
  • Ridgeway, Larry D.
  • Morse, Steve J.
  • Lazar, Michael A.
  • Hengy, David J.
  • Henderson, James H.

Abrégé

Disclosed herein is a duplicator assembly for forming a first void, which can be layered, in a laminated material of a part that matches a second void in a scarf repair guide. The duplicator assembly comprises an arm that comprises a first end portion and a second end portion. The first end portion is spaced apart from the second end portion. The duplication assembly also comprises a probe that is fixed to the first end portion of the arm and configured to trace the second void in the scarf repair guide. The duplication assembly further comprises a milling tool that is fixed to the second end portion of the arm such that the milling tool is co- movably coupled with the probe via the arm.

Classes IPC  ?

  • B29C 73/04 - 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
  • B29C 73/24 - Appareils ou accessoires non prévus ailleurs

70.

DUAL-INDEPENDNT HYBRID ACTUATOR SYSTEM

      
Numéro de document 03106788
Statut En instance
Date de dépôt 2021-01-21
Date de disponibilité au public 2021-09-23
Propriétaire THE BOEING COMPANY (USA)
Inventeur(s)
  • Blanding, David E.
  • Coffman, Jeffrey C.
  • Quiambao, Jimmy M.

Abrégé

A dual-independent hybrid actuator system includes an actuator body defining a hydraulic chamber. The actuator system includes a hydraulic piston assembly, including a hydraulic piston disposed within the hydraulic chamber and dividing the hydraulic chamber into a first hydraulic sub-chamber in fluid communication with a first hydraulic fluid passage and a second hydraulic sub-chamber in fluid communication with a second hydraulic fluid passage. The actuator system further includes a piston rod mounted to the hydraulic piston that passes through the second hydraulic sub-chamber with a distal end that projects outward from the actuator body. The actuator system further includes an electric motor mounted to the actuator body, and a threaded axle mechanically coupled to a motor shaft of the electric motor. The threaded axle passes through the first hydraulic sub-chamber and engages with a threaded port formed in the hydraulic piston assembly.

Classes IPC  ?

  • F16H 47/00 - Combinaisons d'une transmission mécanique avec des embrayages à fluide ou une transmission à fluide
  • B64C 13/42 - Dispositifs de transmission avec amplification de puissance utilisant la pression d'un fluide comportant des dispositifs de doublement de la commande ou de mise en position de secours
  • B64C 13/50 - Dispositifs de transmission avec amplification de puissance utilisant l'énergie électrique
  • F15B 15/14 - Dispositifs actionnés par fluides pour déplacer un organe d'une position à une autre; Transmission associée à ces dispositifs caractérisés par la structure de l'ensemble moteur le moteur étant du type à cylindre droit
  • F15B 15/20 - Autres parties constitutives
  • F15B 20/00 - Dispositions propres à la sécurité pour systèmes de manœuvre utilisant les fluides; Utilisation des dispositifs de sécurité dans les systèmes de manœuvre utilisant des fluides; Mesures d'urgence pour les systèmes de manœuvre utilisant des fluides

71.

METHOD OF RAPID CONVERSION OF CHEMICAL ENERGY INTO USABLE ELECTRICAL ENERGY

      
Numéro de document 03110717
Statut En instance
Date de dépôt 2021-02-26
Date de disponibilité au public 2021-09-20
Propriétaire THE BOEING COMPANY (USA)
Inventeur(s) Grossnickle, James A.

Abrégé

A system using Faraday's law to rapidly direct convert the kinetic energy of a magnetized and/or conducting projectile into usable electrical energy. The system includes a barrel comprising a bore; a circuit including a plurality of electrically conductive components distributed along a length of the bore; and a projectile comprising at least one of a conductive material or a magnetic material magnetically coupled to the electrically conductive components when the projectile is moving along the length of the bore. The circuit stores energy generated from an electric current induced in the electrically conductive components when the projectile moving along the length of the bore causes a magnetic interaction between the electrically conductive components and the magnetic material or the conductive material. The magnetic interaction also causes braking of the projectile.

Classes IPC  ?

  • F41A 35/00 - Accessoires ou détails non prévus ailleurs
  • F41A 21/00 - Tubes d'arme; Accessoires de bouches de canon; Montage des tubes d'arme
  • H02J 7/00 - Circuits pour la charge ou la dépolarisation des batteries ou pour alimenter des charges par des batteries
  • H02K 7/18 - Association structurelle de génératrices électriques à des moteurs mécaniques d'entraînement, p.ex. à des turbines

72.

COMPRESSION FIT EME PROTECTION SEAL CAP

      
Numéro de document 03110955
Statut En instance
Date de dépôt 2021-02-25
Date de disponibilité au public 2021-09-16
Propriétaire THE BOEING COMPANY (USA)
Inventeur(s)
  • Cowan, Daniel J.
  • Stevens, Bart

Abrégé

A protection seal cap for enclosing an end portion of a fastener which extends from a structure, which includes a cap member, which includes a sidewall that defines an interior space within the cap member. The sidewall forms a continuous wall member positioned within the cap member. The continuous wall member defines an opening providing access to the interior space. The continuous wall member is configured to create an interference compression fit between the end portion of the fastener and the continuous wall member.

Classes IPC  ?

  • F16B 37/14 - Ecrous-chapeaux; Chapeaux d'écrous ou de boulons
  • B64C 1/00 - Fuselages; Caractéristiques structurales communes aux fuselages, voilures, surfaces stabilisatrices ou organes apparentés
  • B64D 45/02 - Dispositifs de protection contre la foudre; Déperditeurs de potentiel

73.

CONTROL SURFACE ACTUATOR ASSEMBLIES, AIRCRAFT HYDRAULIC SYSTEMS INCLUDING THE SAME, AND ASSOCIATED AIRCRAFT AND METHODS

      
Numéro de document 03109840
Statut En instance
Date de dépôt 2021-02-19
Date de disponibilité au public 2021-09-06
Propriétaire THE BOEING COMPANY (USA)
Inventeur(s)
  • Roach, Jeffrey M.
  • Fox, Michael Thomas

Abrégé

Control surface actuator assemblies, aircraft hydraulic systems including the same, and associated aircraft and methods. A control surface actuator assembly includes a flight control surface operatively coupled to a support structure, a torque- generating hydraulic actuator configured to apply a torque to pivot the flight control surface, and a variable horn radius (VHR) hydraulic actuator configured to vary an actuator moment arm length for pivoting the flight control surface. In some examples, an aircraft hydraulic system includes such control surface actuator assemblies, and an aircraft includes such aircraft hydraulic systems. In some examples, a method of operating one or more flight control surfaces of an aircraft includes controlling a selected flight control surface by adjusting, with a VHR hydraulic actuator, an actuator moment arm length corresponding to the selected flight control surface and pivoting, with a torque-generating hydraulic actuator, the selected flight control surface.

Classes IPC  ?

  • B64C 13/40 - Dispositifs de transmission avec amplification de puissance utilisant la pression d'un fluide

74.

METHODS AND DEVICES FOR SUPPORTING OF VARIETY OF DIFFERENT PRE-CURED COMPOSITE STRINGERS

      
Numéro de document 03107266
Statut En instance
Date de dépôt 2021-01-26
Date de disponibilité au public 2021-08-26
Propriétaire THE BOEING COMPANY (USA)
Inventeur(s)
  • Knutson, Samuel J.
  • Kendall, James R.
  • Suriyaarachchi, Raviendra S.

Abrégé

Provided are methods and devices for supporting of variety of different pre- cured composite stringers after forming and prior to curing. A post-forming processing device comprises a base with a channel for receiving hat portions of different stringers. The device also comprises a support structure, at least partially extending within the channel. The support structure is configured to conform to different hat portions and to retain the shape of these hat portions. For example, the support structure is made from a flexible material, which conforms to any shape variations. In some examples, the support structure is made from a jamming material that is reshaped together with each of the pre- cured composite stringers. A post-forming processing device is used for supporting different pre- cured composite stringers while various operations are performed on these stringers, such as stringer trimming, inspection, installation of bladders and noodles, and the like.

Classes IPC  ?

  • B29C 70/40 - Façonnage ou imprégnation par compression

75.

PART EDGE SEAL ARRANGEMENT AND JOINING METHOD

      
Numéro de document 03101416
Statut En instance
Date de dépôt 2020-12-02
Date de disponibilité au public 2021-08-25
Propriétaire THE BOEING COMPANY (USA)
Inventeur(s)
  • Wu, Steven Kuan-Chi
  • Schroeder, Ian Edward
  • Shadell, Mark Edmond
  • Uhlman, Melissa A.
  • Wiseman, Jesse Randal
  • Dang, Tho Ngoc
  • Tanner, Richard Bruce
  • Miller, Melinda Dae
  • Talcott, Kristopher William

Abrégé

A seal arrangement is provided for sealing an exposed edge of a composite laminate part having a fay surface configured to be joined to a structure. The seal arrangement includes a precured edge seal covering the exposed edge and a cover covering the edge seal. A seal bead located within a recess in the fay surface of the part forms a seal between the part and the structure.

Classes IPC  ?

  • F16J 15/02 - Joints d'étanchéité entre surfaces immobiles entre elles
  • B64F 5/10 - Fabrication ou assemblage d’aéronefs, p.ex. gabarits à cet effet
  • B29C 65/48 - Assemblage d'éléments préformés; Appareils à cet effet en utilisant des adhésifs
  • B64C 1/06 - Cadres; Lisses; Longerons

76.

ROTARY ACTUATOR

      
Numéro de document 03107262
Statut En instance
Date de dépôt 2021-01-26
Date de disponibilité au public 2021-08-24
Propriétaire THE BOEING COMPANY (USA)
Inventeur(s)
  • Standley, John A.
  • Lisenko, Kim R.
  • Zazynski, Timothy Paul

Abrégé

A rotary actuator, including a manifold block and a rotor assembly that includes a rotor shaft and a plurality of arcuate pistons attached to the rotor shaft, each arcuate piston curving at a set radial distance from the rotor shaft, and each piston attached to the rotor shaft via a crank arm. A pressure chamber assembly coupled to the manifold block defines a plurality of piston pressure chambers that receive and at least partially enclose each arcuate piston, including a plurality of gland seals disposed adjacent the entrance of each piston pressure chamber to create a seal between the inner surface of the pressure chamber and the outer surface of the arcuate piston. Each gland seal includes an inner seal that engages the piston surface of the arcuate piston, and plural outer seals that engage the inner surface of the piston pressure chamber, forming a hydraulic seal.

Classes IPC  ?

  • F03C 1/00 - Machines motrices à liquide à pistons alternatifs
  • B64C 13/40 - Dispositifs de transmission avec amplification de puissance utilisant la pression d'un fluide

77.

SYSTEMS AND METHODS FOR DETERMINING SPACE AVAILABILITY IN AN AIRCRAFT

      
Numéro de document 03102512
Statut En instance
Date de dépôt 2020-12-10
Date de disponibilité au public 2021-08-21
Propriétaire THE BOEING COMPANY (USA)
Inventeur(s)
  • Patel, Amar
  • Patel, Vinutha

Abrégé

An example system for determining space availability in an aircraft includes a plurality of laser sensors configured to be positioned in a baggage container at a first wall and a second wall, and the first wall and the second wall face each other. The plurality of laser sensors emit signals within the baggage container and detect reflected responses to generate outputs. The system also includes one or more processors in communication with the plurality of laser sensors for executing instructions stored in non- transitory computer readable media to perform functions including receiving the outputs from the plurality of laser sensors, mapping contents of the baggage container based on the outputs from the plurality of laser sensors, and based on said mapping, outputting data indicative of occupied space in the baggage container.

Classes IPC  ?

  • B64D 47/00 - Equipements non prévus ailleurs
  • B64D 9/00 - Appareillage pour manutention du fret; Appareillage pour faciliter l'embarquement des passagers ou autres
  • B64D 11/00 - Arrangements pour passagers ou équipage; Installations de postes de pilotage non prévues ailleurs
  • G01S 17/88 - Systèmes lidar, spécialement adaptés pour des applications spécifiques
  • G01S 7/51 - Dispositions pour l'affichage

78.

FUSELAGE STRUCTURE SPLICE

      
Numéro de document 03107492
Statut En instance
Date de dépôt 2021-01-29
Date de disponibilité au public 2021-08-21
Propriétaire THE BOEING COMPANY (USA)
Inventeur(s)
  • Stoddard, Zachary Nathaniel
  • Mcghee, Ronald Leroy

Abrégé

A fuselage structure splice may include a panel having an edge and a strap connected to the first panel along the panel edge. A strap surface not in contact with the panel tapers toward the panel with distance from the panel edge. A stringer is mounted on the panel and extends away from the edge of the panel and has a flange mounted to the panel. A fitting has a stringer base portion and a strap base portion. The stringer base portion is connected to the stringer flange and extends along a first line extending in a plane normal to the panel edge. The strap base portion of the fitting is mounted on the strap surface and extends along a second line in the plane. The second line is transverse to the first line and the strap base portion of the fitting has a constant thickness along the second line.

Classes IPC  ?

  • B64C 1/00 - Fuselages; Caractéristiques structurales communes aux fuselages, voilures, surfaces stabilisatrices ou organes apparentés
  • B64F 5/10 - Fabrication ou assemblage d’aéronefs, p.ex. gabarits à cet effet

79.

METHODS FOR FABRICATING SOLID LAMINATE STRINGERS ON A COMPOSITE PANEL

      
Numéro de document 03101081
Statut En instance
Date de dépôt 2020-11-27
Date de disponibilité au public 2021-08-18
Propriétaire THE BOEING COMPANY (USA)
Inventeur(s) Cheng, Jiangtian

Abrégé

A method of fabricating a solid laminate stringer on a composite panel, including unspooling one or more composite layers onto the composite panel; compacting the one or more composite layers unspooled onto the composite panel; cutting the one or more composite layers unspooled onto the composite panel; and curing the one or more composite layers unspooled onto the composite panel, wherein the one or more composite layers are unspooled continuously along a length corresponding to a length of the solid laminate stringer.

Classes IPC  ?

  • B29C 64/147 - Procédés de fabrication additive n’utilisant que des matériaux solides utilisant des matériaux stratifiés, p.ex. fabrication d’objets stratifiés ou matériau stratifié prédécoupé selon les sections en coupe de l’objet en 3D
  • B33Y 40/00 - Opérations ou équipements auxiliaires, p.ex. pour la manipulation de matériau
  • B32B 27/04 - Produits stratifiés composés essentiellement de résine synthétique comme substance d'imprégnation, de collage, ou d'enrobage
  • 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 38/18 - Manipulation des couches ou du stratifié
  • B32B 41/00 - Dispositions pour le contrôle ou la commande des procédés de stratification; Dispositions de sécurité
  • B64C 3/18 - Longerons; Nervures; Lisses
  • C08J 5/04 - Renforcement des composés macromoléculaires avec des matériaux fibreux en vrac ou en nappes
  • C08J 5/24 - Imprégnation de matériaux avec des prépolymères pouvant être polymérisés en place, p.ex. fabrication des "prepregs"

80.

COMPOSITE PLANK SUPPORT FOR STRINGER PANEL

      
Numéro de document 03106794
Statut En instance
Date de dépôt 2021-01-21
Date de disponibilité au public 2021-08-18
Propriétaire THE BOEING COMPANY (USA)
Inventeur(s) Clark, Gregory L.

Abrégé

Provided are stiffened stringer panels with integrated plank structures. An example composite panel comprises a skin member having an inner surface, and a plank on the inner surface. The plank comprises a set of layered laminate plies and extends from a first side to a second side. Each laminate ply of the set of layered laminate plies is sized to form a desired geometric profile for each of the first side and the second side. The composite panel further comprises a stringer including a cap portion that spans from the first side of the plank to the second side of the plank to form a first flange portion and a second flange portion, respectively, on the inner surface of the skin member. Base segments of the cap portion conform to the desired geometric profile of respective first and second sides of the plank.

Classes IPC  ?

  • B64C 1/06 - Cadres; Lisses; Longerons
  • B64F 5/10 - Fabrication ou assemblage d’aéronefs, p.ex. gabarits à cet effet
  • B29C 70/18 - Façonnage de matières composites, c. à d. de matières plastiques comprenant des renforcements, des matières de remplissage ou des parties préformées, p.ex. des inserts comprenant uniquement des renforcements, p.ex. matières plastiques auto-renforçantes des renforcements fibreux uniquement caractérisées par la structure des renforcements fibreux utilisant des fibres de grande longueur, ou des fibres continues sous forme d'un mat, p.ex. préimprégné [SMC]
  • B64C 1/12 - Structure ou fixation de panneaux de revêtement

81.

AIRLINE CATERING TROLLEY

      
Numéro de document 03107260
Statut En instance
Date de dépôt 2021-01-26
Date de disponibilité au public 2021-08-14
Propriétaire THE BOEING COMPANY (USA)
Inventeur(s) Stephens, Gentry B.

Abrégé

An airline catering trolley includes a mobile cart body, a beverage dispensing system disposed within the cart body, and a computing device mounted to the cart body and operatively connected to the beverage dispensing system. The beverage dispensing system includes a beverage dispenser extending from the cart body. The computing device includes a processor, a memory, an input/output device, and a transceiver, and is configured to receive a first input regarding a beverage to be dispensed through the input/output device, dispense a beverage from the beverage dispenser based on the first input, and communicate service data regarding operation of the airline catering trolley to an aircraft computing system of an aircraft.

Classes IPC  ?

  • A47B 31/06 - Tables de desserte ou à thé, chariots ou tables roulantes conçus pour être utilisés dans des véhicules
  • B64D 11/00 - Arrangements pour passagers ou équipage; Installations de postes de pilotage non prévues ailleurs
  • B67D 1/00 - Appareils ou dispositifs pour débiter des boissons à la pression

82.

CONFIGURABLE ERGONOMIC PAD

      
Numéro de document 03108559
Statut En instance
Date de dépôt 2021-02-10
Date de disponibilité au public 2021-08-13
Propriétaire THE BOEING COMPANY (USA)
Inventeur(s) Cook, Rebecca

Abrégé

An ergonomic pad includes a bladder formed of a pliable material and a granular material disposed within the bladder and at least partially filling the bladder. A port is coupled to the bladder and configured to enable evacuation of air from the bladder. The bladder also includes a sealable opening distinct from the port to add or remove the granular material.

Classes IPC  ?

  • A47C 16/00 - Appuis ou supports pour les pieds, les jambes, les bras, le dos ou la tête
  • A47C 9/02 - Tabourets de bureau; Tabourets d'atelier

83.

LOW COST, HIGH PERFORMANCE, MULTI-HEAD DRILL AND FILL MACHINE

      
Numéro de document 03108446
Statut En instance
Date de dépôt 2021-02-08
Date de disponibilité au public 2021-08-10
Propriétaire THE BOEING COMPANY (USA)
Inventeur(s) Kismarton, Max U.

Abrégé

A manufacturing system employing a bifurcated backbone having an upper plate and lower plate, with a longitudinal slot between the upper and lower plate. A plurality of actuator groups are mounted longitudinally adjacent the slot. A carrier supports a panel for longitudinal translation into the slot and the carrier is configured to pulse longitudinally in the slot relative to the plurality of actuator groups during a sequence of fabrication operations by the plurality of actuator groups on the panel.

Classes IPC  ?

  • B23Q 39/00 - Machines pour le travail des métaux incorporant un grand nombre de sous-ensembles capables chacun de réaliser une opération de travail du métal
  • B23P 23/04 - Machines ou agencements de machines réalisant des combinaisons déterminées de différentes opérations d'usinage, non couverts par une seule autre sous-classe pour effectuer l'usinage ainsi que les autres opérations de travail du métal

84.

JOINT ASSEMBLY HAVING SHIMMED BOSSES AND ASSOCIATED METHOD OF MAKING THE JOINT ASSEMBLY

      
Numéro de document 03106154
Statut En instance
Date de dépôt 2021-01-14
Date de disponibilité au public 2021-08-06
Propriétaire THE BOEING COMPANY (USA)
Inventeur(s)
  • Whitmer, Brett D.
  • Graham, William H.
  • Van Ingelghem, Evelyne

Abrégé

An assembly comprises a first part and a second part. The second part comprises a non-faying surface facing the base surface, a plurality of faying surfaces manifested at bosses that are shimmed if and as required, and a plurality of second through- holes. A width of each one of the plurality of bosses is equal to or greater than 2(r + Ttane), where r is a maximum radial dimension of an outermost peripheral portion of a fastener in contact with the first part or the second part, T is the distance from the point of contact, between a fastener and the first part or the second part, and a faying surface of a corresponding boss, and e is an angle between a central axis of the corresponding second through-hole and an outermost load vector initiating at the point of contact between the fastener and the first part or the second part.

Classes IPC  ?

  • F16B 5/00 - Jonction de feuilles ou de plaques soit entre elles soit à des bandes ou barres parallèles à elles
  • B64F 5/10 - Fabrication ou assemblage d’aéronefs, p.ex. gabarits à cet effet
  • B64C 1/00 - Fuselages; Caractéristiques structurales communes aux fuselages, voilures, surfaces stabilisatrices ou organes apparentés

85.

COMPOSITE ASSEMBLY WITH INTEGRALLY FORMED PANELS AND STIFFENERS

      
Numéro de document 03102843
Statut En instance
Date de dépôt 2020-12-14
Date de disponibilité au public 2021-08-04
Propriétaire THE BOEING COMPANY (USA)
Inventeur(s)
  • Robbins, Kevin Larry
  • Lauder, Arnold John
  • Ramrattan, Mahendra

Abrégé

A composite assembly that includes one or more panels and integral stiffeners. The composite assembly is formed from multiple composite plies that form the one or more panels and stiffeners. The construction process uses multiple tool segments that each replicate a section of the composite assembly. Composite plies are positioned on each tool segment and then the tool segments and their composite plies are placed together. Sections of the plies that extend along the faces of the tool segments form the panel. Sections of the composite plies that extend along lateral sides of the tool segments form the stiffeners. Additional composite plies are laid up over the tool segments and composite plies to complete the process. The composite plies are then cured to form the finished composite assembly.

Classes IPC  ?

  • B29C 70/02 - Façonnage de matières composites, c. à d. de matières plastiques comprenant des renforcements, des matières de remplissage ou des parties préformées, p.ex. des inserts comprenant des combinaisons de renforcements et de matières de remplissage dans une matrice, formant une ou plusieurs couches, avec ou sans couches non renforcées ou non remplies
  • B64F 5/10 - Fabrication ou assemblage d’aéronefs, p.ex. gabarits à cet effet
  • B29C 70/24 - Façonnage de matières composites, c. à d. de matières plastiques comprenant des renforcements, des matières de remplissage ou des parties préformées, p.ex. des inserts comprenant uniquement des renforcements, p.ex. matières plastiques auto-renforçantes des renforcements fibreux uniquement caractérisées par la structure des renforcements fibreux utilisant des fibres de grande longueur, ou des fibres continues orientées dans au moins trois directions formant une structure tridimensionnelle
  • B64C 7/00 - Structures ou carénages non prévus ailleurs

86.

ASSEMBLY TO CONNECT A PANEL TO A SUPPORT MEMBER

      
Numéro de document 03100936
Statut En instance
Date de dépôt 2020-11-25
Date de disponibilité au public 2021-07-31
Propriétaire THE BOEING COMPANY (USA)
Inventeur(s)
  • Files, Joe
  • Cartwright, Jeffrey Allen
  • Logue, Adam Arthur
  • Fowler, Robert B.

Abrégé

ABSTRACT An assembly to connect a panel to a support member. The assembly may include a saddle fitting configured to connect to the support member and including first and second plates. A back fitting may be positioned between the second plate of the saddle fitting and a second face of the panel. An index fitting includes a flange that may be positioned between the first plate of the saddle fitting and a first face of the panel, and a boss that extends outward from the flange and through the opening in the panel. The index fitting is wider than the panel and sized to fit within the gap of the saddle fitting with a first end of the index fitting contacting against the first plate and a second end of the index fitting contacting against the second plate. One or more fasteners may connect the saddle fitting to the index fitting. Date Recue/Date Received 2020-11-25

Classes IPC  ?

  • F16B 1/00 - Dispositifs pour assembler des éléments structuraux ou parties de machines ou bien pour empêcher tout mouvement relatif entre eux
  • B64C 1/00 - Fuselages; Caractéristiques structurales communes aux fuselages, voilures, surfaces stabilisatrices ou organes apparentés

87.

REACTIVATION OF CO-CURED FILM LAYERS

      
Numéro de document 03106805
Statut En instance
Date de dépôt 2021-01-22
Date de disponibilité au public 2021-07-24
Propriétaire THE BOEING COMPANY (USA)
Inventeur(s)
  • Brei, Mark R.
  • Gordon, Kevin D.
  • Garnier, Christopher

Abrégé

ABSTRACT The present disclosure is directed to a method for reactivating a co-cured film layer disposed on a composite structure, the method comprising applying a reactivation treatment composition comprising at least two solvents and a surface exchange agent comprising a metal alkoxide or chelate thereof to the co-cured film layer, and allowing the reactivation treatment composition to create a reactivated co-cured film layer, wherein the co-cured film layer was previously cured at a curing temperature greater than about 50 C. A reactivated co-cured film layer and an aircraft part having a reactivated co-cured film layer are also provided. Date Recue/Date Received 2021-01-22

Classes IPC  ?

  • C08J 7/02 - Traitement chimique ou revêtement d'objets façonnés faits de substances macromoléculaires par des solvants, p.ex. par des agents gonflants
  • C08J 7/043 - Amélioration de l'adhésivité des revêtements en soi, p.ex. par formation d'apprêts

88.

ELECTRICAL POWER GENERATION FROM TURBINE ENGINES

      
Numéro de document 03100622
Statut En instance
Date de dépôt 2020-11-25
Date de disponibilité au public 2021-07-16
Propriétaire THE BOEING COMPANY (USA)
Inventeur(s) Liu, Shengyi

Abrégé

Electrical power generation in turbine engines in provided by a permanent magnet that emits a first magnetic field and is disposed on a first rotor assembly of a turbine engine; an armature winding connected to a second rotor assembly of the turbine engine such that the armature winding is positioned within the first magnetic field; a resonant emitter configured to receive an electrical power input from the armature winding to generate a second magnetic field of at least a predefined frequency when the first rotor assembly rotates relative to the second rotor assembly; and a resonant receiver disposed on an enclosure of the turbine engine, positioned to receive the second magnetic field and convert the second magnetic field into an electrical power output.

Classes IPC  ?

  • H02K 16/02 - Machines avec un stator et deux rotors
  • F01D 15/10 - Adaptations pour la commande des générateurs électriques ou combinaisons avec ceux-ci
  • 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
  • H02K 1/06 - MACHINES DYNAMO-ÉLECTRIQUES - Détails du circuit magnétique caractérisés par la configuration, la forme ou le genre de structure
  • H02K 7/18 - Association structurelle de génératrices électriques à des moteurs mécaniques d'entraînement, p.ex. à des turbines

89.

LIGHTNING DAMAGE RESISTANT ONE SIDED INSTALLATION

      
Numéro de document 03102499
Statut En instance
Date de dépôt 2020-12-10
Date de disponibilité au public 2021-07-13
Propriétaire THE BOEING COMPANY (USA)
Inventeur(s) Shahriar, Khosravani

Abrégé

ABSTRACT A fastener assembly includes a bolt having a head and having a shank. The shank defines threads, the bolt defines a channel which extends circumferentially about the bolt, and the head defines multiple head channels with a first end of each of the multiple head channels in communication with the channel and a second end of each of the multiple head channels in communication with an outside of the head positioned at a top surface of the head. The fastener assembly further includes a sleeve having threads compatible for engaging the threads of the bolt. The sleeve includes a portion of the sleeve including an annealed material and multiple slots defined through the sleeve. With the bolt positioned within the sleeve, each of the multiple slots defined through the sleeve is positioned in communication with the channel. Date Recue/Date Received 2020-12-10

Classes IPC  ?

  • F16B 29/00 - Assemblage à vis avec déformation de l'écrou ou d'un organe auxiliaire pendant la fixation
  • B64C 1/12 - Structure ou fixation de panneaux de revêtement
  • B64C 3/26 - Construction, forme ou fixation des revêtements distincts, p.ex. panneaux
  • B64D 45/02 - Dispositifs de protection contre la foudre; Déperditeurs de potentiel
  • F16B 13/12 - Chevilles métalliques creuses bloquées par insertion d'un clou, d'une vis ou d'une pièce similaire
  • F16B 19/10 - Rivets creux; Rivets en plusieurs morceaux fixés par action mécanique
  • F16B 23/00 - Têtes de boulons ou de vis de forme spéciale pour permettre leur rotation à l'aide d'un outil
  • F16B 37/06 - Dispositifs pour fixer les écrous à des surfaces, p.ex. à des feuilles, à des plaques par soudage ou rivetage

90.

SYSTEM AND METHOD FOR ENCRYPTED RESONANT INDUCTIVE POWER TRANSFER

      
Numéro de document 03105100
Statut En instance
Date de dépôt 2021-01-07
Date de disponibilité au public 2021-07-10
Propriétaire THE BOEING COMPANY (USA)
Inventeur(s) Tillotson, Brian J.

Abrégé

ABSTRACT Systems and methods for ensuring that resonant inductive power transfer goes only to authorized users using encryption. Resonant inductive power transfer requires near-identical resonant frequencies in the transmitter and the receiver. The frequency of the power transfer signal changes on a schedule known only to the transmitter (1) and receiver (3) so a "power eavesdropper" cannot track the frequency well enough to efficiently receive power. To make the frequency transitions energetically efficient, a capacitive or inductive element is switched in or out of each circuit at moments of zero- crossing: zero charge on a capacitor or zero current in an inductor. To maintain phase alignment, either switching an inductor (2b) on the transmit side is nearly simultaneous with switching a capacitor (8b) on the receive side, or switching a capacitor (6b) on the transmit side is nearly simultaneous with switching an inductor (4b) on the receive side. Date Recue/Date Received 2021-01-07

Classes IPC  ?

  • H02J 50/12 - Circuits ou systèmes pour l'alimentation ou la distribution sans fil d'énergie électrique utilisant un couplage inductif du type couplage à résonance
  • H02J 50/80 - Circuits ou systèmes pour l'alimentation ou la distribution sans fil d'énergie électrique mettant en œuvre l’échange de données, concernant l’alimentation ou la distribution d’énergie électrique, entre les dispositifs de transmission et les dispositifs de réception
  • H01F 5/00 - Bobines d'induction
  • H01F 38/14 - Couplages inductifs

91.

OPERATIONS CLOCK FACTORY

      
Numéro de document 03100938
Statut En instance
Date de dépôt 2020-11-25
Date de disponibilité au public 2021-07-06
Propriétaire THE BOEING COMPANY (USA)
Inventeur(s) Adamson, Chad R.

Abrégé

ABSTRACT A factory for assembling aircraft or other systems includes a factory floor with multiple build stations. The factory floor includes a hub-and-spoke tool track having radial track sections connected to and extending radially from a circular center hub section. Each track section terminates at a respective build station. A mobile transport travels along the track to the build stations, transforms into different join tools at a predetermined build station, and thereafter engages and supports the components. An overhead crane may perform another task at each build station. The factory floor may include a first floor positioned below a smaller diameter second floor with ramps interconnecting the floors. A center tower is surrounded by the floor(s), with the center tower defining rooms. An aircraft may be assembled via a method using the above- noted factory. Date Recue/Date Received 2020-11-25

Classes IPC  ?

  • B64F 5/10 - Fabrication ou assemblage d’aéronefs, p.ex. gabarits à cet effet

92.

TUNED MULTILAYERED MATERIAL SYSTEMS AND METHODS FOR MANUFACTURING

      
Numéro de document 03098381
Statut En instance
Date de dépôt 2020-11-06
Date de disponibilité au public 2021-07-03
Propriétaire THE BOEING COMPANY (USA)
Inventeur(s) Yousefiani, Ali

Abrégé

ABSTRACT A graded multilayered composite (1100) comprises a metal matrix material (1110), having a first side (1112) and a second side (1114), opposite the first side (1112). A first layer (1120) of microspheres is dispersed on the first side (1112) of the metal matrix material (1110). A second layer (1122) of microspheres is dispersed on the second side (1114) of the metal matrix material (1110). Date Recue/Date Received 2020-11-06

Classes IPC  ?

  • B32B 5/16 - Produits stratifiés caractérisés par l'hétérogénéité ou la structure physique d'une des couches caractérisés par le fait qu'une des couches est formée de particules, p.ex. de copeaux, de fibres hachées, de poudre
  • B32B 5/30 - 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 comprenant des grains ou de la poudre
  • B32B 15/16 - Produits stratifiés composés essentiellement de métal adjacent à une couche particulaire

93.

SYSTEMS AND METHODS FOR INSPECTING ADDITIVELY MANUFACTURED COMPONENTS

      
Numéro de document 03096921
Statut En instance
Date de dépôt 2020-10-21
Date de disponibilité au public 2021-07-02
Propriétaire THE BOEING COMPANY (USA)
Inventeur(s)
  • Sanders, Daniel G.
  • Hull, John R.
  • Georgeson, Gary E.

Abrégé

ABSTRACT A system and method for inspecting an additively manufactured component include an additive manufacturing head configured to form a component layer-by- layer, and an electromagnetic acoustic transducer (EMAT) configured to inspect one or more layers of the component. Date Recue/Date Received 2020-1 0-2 1

Classes IPC  ?

  • G01S 15/89 - Systèmes sonar, spécialement adaptés à des applications spécifiques pour la cartographie ou la représentation
  • B33Y 50/02 - Acquisition ou traitement de données pour la fabrication additive pour la commande ou la régulation de procédés de fabrication additive

94.

MOLDING SYSTEM AND METHODS FOR FORMING STRUCTURES

      
Numéro de document 03099591
Statut En instance
Date de dépôt 2020-11-17
Date de disponibilité au public 2021-07-02
Propriétaire THE BOEING COMPANY (USA)
Inventeur(s)
  • Lockett, Peter J.
  • Scarfe, Manning

Abrégé

ABSTRACT A molding system and methods of forming a structure are presented. A molding system is configured to form a composite structure. The molding system comprises a first tool comprising a first vacuum groove, a first trough having a first edge configured to form a first bend of the composite structure, and a first molding surface; and a second tool comprising a second vacuum groove, a second trough having a second edge configured to form a second bend of the composite structure, and a second molding surface. Date Recue/Date Received 2020-11-17

Classes IPC  ?

  • B29C 43/12 - Pressage isostatique, c. à d. en utilisant des organes presseurs non rigides coopérant avec des organes rigides ou des matrices utilisant des sacs entourant la matière à mouler
  • B29C 70/36 - Façonnage par empilage, c.à d. application de fibres, de bandes ou de feuilles larges sur un moule, un gabarit ou un noyau; Façonnage par pistolage, c.à d. pulvérisation de fibres sur un moule, un gabarit ou un noyau et imprégnation par coulée, p.ex. coulée sous vide

95.

AIRCRAFT LANDING GEAR FORWARD TRUNNION SUPPORT ASSEMBLIES, TRUNNION HOUSINGS AND RELATED METHODS

      
Numéro de document 03101719
Statut En instance
Date de dépôt 2020-12-04
Date de disponibilité au public 2021-07-02
Propriétaire THE BOEING COMPANY (USA)
Inventeur(s)
  • Palmer, Ben J.
  • Cazin, Ryan J.

Abrégé

ABSTRACT Aircraft landing gear forward trunnion support assemblies and related methods are described herein. An example aircraft wing disclosed herein includes a rear spar having a rear side and a front side opposite the rear side and a forward trunnion support assembly. The forward trunnion support assembly includes first and second vertical support fittings coupled to the rear side of the rear spar, and a trunnion housing with a bearing. The trunnion housing is coupled between the first and second vertical support fittings. The trunnion housing also includes first and second shoulders formed on a top side of the trunnion housing, each of the first and second shoulders having a respective channel formed on a respective top portion thereof. A fuse pin is received within the channels and has a first end extending through the first vertical support fitting and a second end extending through the second vertical support fitting. Date Recue/Date Received 2020-12-04

Classes IPC  ?

  • B64C 25/10 - Atterrisseurs non fixes, p.ex. largables escamotables, repliables ou ayant un mouvement apparenté
  • B64C 3/00 - Voilures

96.

JOINT JOINING AN AIRCRAFT WING TO AN AIRCRAFT BODY

      
Numéro de document 03100811
Statut En instance
Date de dépôt 2020-11-26
Date de disponibilité au public 2021-06-20
Propriétaire THE BOEING COMPANY (USA)
Inventeur(s)
  • Mclaughlin, Mark R.
  • Young, Jenny
  • Keefe, Drew-Daniel T.
  • Lockin, Charles B.
  • Leibov, David H.

Abrégé

ABSTRACT [0051]A joint joining an aircraft wing to an aircraft body employs a splice panel that is engaged in surface engagement with a skin panel on a side of the aircraft body and is engaged in surface engagement with a leg panel extending upwardly from the aircraft wing. A plurality of fasteners extend through the splice panel and the leg panel and extend through the splice panel and the skin panel. The plurality of fasteners attach the splice panel to the skin panel and attach the splice panel to the leg panel and thereby attach the skin panel to the leg panel. After fastener holes have been drilled through the splice panel and the leg panel to attach the splice panel to the leg panel, the splice panel can be removed from the leg panel. This provides easy access to the fastener holes drilled through the leg panel for deburring of the fastener holes. Date Recue/Date Received 2020-11-26

Classes IPC  ?

  • B64C 1/26 - Fixation de la voilure, des empennages ou des surfaces stabilisatrices

97.

LONGITUDINAL BEAM JOINT FOR A PRESSURE DECK ASSEMBLY

      
Numéro de document 03102718
Statut En instance
Date de dépôt 2020-12-15
Date de disponibilité au public 2021-06-16
Propriétaire THE BOEING COMPANY (USA)
Inventeur(s)
  • Mclaughlin, Mark R.
  • Ingham, Steven D.
  • Cox, Daniel J.
  • Lockin, Charles B.
  • Vukosav, Danilo

Abrégé

ABSTRACT A pressure deck assembly for a fuselage includes a longitudinal beam extending a length along a roll axis of the fuselage. The longitudinal beam includes a central member and opposing first and second flanges extending from the central member. The first flange includes a first upper side and a first lower side. The second flange includes a second upper side and a second lower side. The pressure deck assembly includes a pressure deck that includes first and second deck segments. The first deck segment is joined to the first flange of the longitudinal beam along the first lower side of the first flange. The second deck segment is joined to the second flange of the longitudinal beam along the second lower side of the second flange. Date Recue/Date Received 2020-12-15

Classes IPC  ?

98.

SOFT TISSUE MATERIAL CUMULATIVE DAMAGE MODEL FOR REDUCING REPETITIVE STRESS INJURIES IN PERFORMING A PROCESS

      
Numéro de document 03158278
Statut En instance
Date de dépôt 2020-12-04
Date de disponibilité au public 2021-06-10
Propriétaire THE BOEING COMPANY (USA)
Inventeur(s)
  • Hammer, Liisa Charlie
  • Cotton, James Dean
  • Gardner, Richard Jay
  • Takatani, Karen Chiyono

Abrégé

Techniques for reducing repetitive stress injuries to soft tissue in performing a process are disclosed. The techniques include obtaining at least one repetitive stress data set related to the soft tissue and to the process; accessing information characterizing a first damage regime and second information characterizing a second damage regime, where the first information quantifies a number of repetitions at a given stress for the soft tissue to transition out of the first damage regime, and wherein the second information quantifies a number of repetitions at a given stress for the soft tissue to transition out of the second damage regime; predicting conditions sufficient for damage to the soft tissue; determining, based on at least the predicting, at least one guideline for reducing a risk of a soft tissue material repetitive stress injury; and implementing the at least one guideline in the process.

Classes IPC  ?

  • A61B 5/00 - Mesure servant à établir un diagnostic ; Identification des individus
  • G16H 20/30 - TIC spécialement adaptées aux thérapies ou aux plans d’amélioration de la santé, p.ex. pour manipuler les prescriptions, orienter la thérapie ou surveiller l’observance par les patients concernant des thérapies ou des activités physiques, p.ex. la physiothérapie, l’acupression ou les exercices
  • G16H 50/20 - TIC spécialement adaptées au diagnostic médical, à la simulation médicale ou à l’extraction de données médicales; TIC spécialement adaptées à la détection, au suivi ou à la modélisation d’épidémies ou de pandémies pour le diagnostic assisté par ordinateur, p.ex. basé sur des systèmes experts médicaux

99.

ARCHED HORIZONTAL PRESSURE DECK TO REAR SPAR GUTTER

      
Numéro de document 03101157
Statut En instance
Date de dépôt 2020-11-30
Date de disponibilité au public 2021-06-06
Propriétaire THE BOEING COMPANY (USA)
Inventeur(s)
  • Mclaughlin, Mark R.
  • Leibov, David H.
  • Paravata, Soma Gopala Rao
  • Menanno, Alfons
  • Vukosav, Danilo

Abrégé

ABSTRACT An arched gutter that can be used to channel moisture within an aircraft can include an arched web including a plurality of laterally spaced arches. The plurality of arches impart a flexibility to the arched gutter such that the arched gutter has an increased resistance to fatigue cracking and other wear and damage resulting from, for example, parasitic loads due to high bending strains that are transferred to the arched gutter by a wing to which the arched gutter is attached during operation of the aircraft. An aircraft section and an aircraft including the arched gutter are also described. Date Recue/Date Received 2020-11-30

Classes IPC  ?

100.

SYSTEM AND METHOD FOR EVALUATING A BOND

      
Numéro de document 03157059
Statut En instance
Date de dépôt 2020-10-09
Date de disponibilité au public 2021-05-06
Propriétaire THE BOEING COMPANY (USA)
Inventeur(s) Safai, Morteza

Abrégé

A system for evaluating a bond includes first and second electrodes. A dielectric material layer is positioned at least partially between the first and second electrodes. A power source is connected to the first and second electrodes. The power source is configured to cause the first and second electrodes to generate an electrical arc. The electrical arc is configured to at least partially ablate a sacrificial material layer to generate a plasma.

Classes IPC  ?

  • B23K 31/12 - Procédés relevant de la présente sous-classe, spécialement adaptés à des objets ou des buts particuliers, mais non couverts par un seul des groupes principaux relatifs à la recherche des propriétés, p.ex. de soudabilité, des matériaux
  • G01M 7/08 - Test de résistance au choc
  • G01N 29/04 - Analyse de solides
  • G01N 29/06 - Visualisation de l'intérieur, p.ex. microscopie acoustique
  • G01N 29/24 - Sondes
  • H05H 1/48 - Production du plasma utilisant un arc
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