An example method is performed by one or more processors of a gateway computing system. The method includes receiving, from a user computing system, a request to access a software application hosted on a server with which the gateway computing system is in communication. The method also includes in response to receiving the request, communicating with the user computing system to obtain a credential for the software application issued to a user of the user computing system. The method also includes comparing the credential to credential data stored on a distributed ledger to determine whether the credential meets a set of conditions. The method also includes in response to determining that the credential meets the set of conditions, establishing an authorized session between the user computing system and the server such that communication between the user computing system and the server passes through the gateway computing system.
Techniques for manufacturing a composite part using a tape laying process are presented. The techniques can include: laying up a preform layer from composite tape; inspecting the preform layer for gaps; comparing the gap measurement with a gap guard band, where the gap guard band is determined by: obtaining anomaly data that includes measurements of fiber that has not been deposited on a respective preform during prior preform lay-up processes; fitting a multi-component model to the anomaly data; simulating a preform manufacture based on the multi-component model; calculating summary statistics on gap width accounting for undetected anomalies; and determining a guard band based on the summary statistics on gap width accounting for undetected anomalies and based on a manufacturing requirement; determining that the preform layer complies with the manufacturing requirement; repeating the laying up, the inspecting, the comparing, and the determining; and heating the preform to form a composite part.
Aspects described herein generally relate to a method of coating a metallic surface. The method includes forming a solution including a corrosion inhibitor having one or more thiol moieties and a hydroxide. The metallic surface is coated with the solution to form a treated metallic surface. The treated metallic surface is further coated with an organosilane, an acid, and a metal alkoxide to form a coating system.
B05D 1/02 - Procédés pour appliquer des liquides ou d'autres matériaux fluides aux surfaces réalisés par pulvérisation
B05D 1/18 - Procédés pour appliquer des liquides ou d'autres matériaux fluides aux surfaces par immersion
B05D 3/02 - Traitement préalable des surfaces sur lesquelles des liquides ou d'autres matériaux fluides doivent être appliquésTraitement ultérieur des revêtements appliqués, p. ex. traitement intermédiaire d'un revêtement déjà appliqué, pour préparer les applications ultérieures de liquides ou d'autres matériaux fluides par cuisson
B05D 3/10 - Traitement préalable des surfaces sur lesquelles des liquides ou d'autres matériaux fluides doivent être appliquésTraitement ultérieur des revêtements appliqués, p. ex. traitement intermédiaire d'un revêtement déjà appliqué, pour préparer les applications ultérieures de liquides ou d'autres matériaux fluides par d'autres moyens chimiques
B05D 7/00 - Procédés, autres que le flocage, spécialement adaptés pour appliquer des liquides ou d'autres matériaux fluides, à des surfaces particulières, ou pour appliquer des liquides ou d'autres matériaux fluides particuliers
C09D 5/00 - Compositions de revêtement, p. ex. peintures, vernis ou vernis-laques, caractérisées par leur nature physique ou par les effets produitsApprêts en pâte
C23F 11/04 - Inhibition de la corrosion de matériaux métalliques par application d'inhibiteurs sur la surface menacée par la corrosion ou par addition d'inhibiteurs à l'agent corrosif dans des liquides à réaction acide marquée
A method includes disposing a joining alloy between a first metal matrix composite substrate and a second metal matrix composite substrate to provide an assembly, and heating the assembly to a melting temperature of the joining alloy for a predetermined period of time. The melting temperature of the joining alloy is less than a melting temperature of the first metal matrix composite substrate and the second metal matrix composite substrate.
A method for fabrication of a layup for a composite honeycomb core sandwich structure includes laying up a first plurality of unidirectional tows over a tool for layup of the composite honeycomb core sandwich structure using an automated fiber placement process to form a stack of under-core composite plies that are tied down to a rough textured surface bonded to the tool; placing a honeycomb core on the stack of under-core composite plies within the rough textured surface; and laying up a second plurality of unidirectional tows over the honeycomb core using the automated fiber placement process to form a stack of over-core composite plies that tie down the honeycomb core to the rough textured surface. The method may also include placing an under-core film adhesive on the stack of under-core composite plies and placing an over-core film adhesive on the honeycomb core.
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
B29C 70/38 - Empilage automatisé, p. ex. utilisant des robots, par application de filaments selon des modèles prédéterminés
B29C 70/44 - Façonnage ou imprégnation par compression pour la fabrication d'objets de longueur définie, c.-à-d. d'objets distincts utilisant une pression isostatique, p. ex. moulage par différence de pression, avec un sac à vide, dans un autoclave ou avec un caoutchouc expansible
B29K 105/08 - Présentation, forme ou état de la matière moulée contenant des agents de renforcement, charges ou inserts de grande longueur, p. ex. ficelles, mèches, mats, tissus ou fils
A lift system and method includes a first clamp assembly, a second clamp assembly, and a gear assembly including one or more gears. The lift system includes a lift housing having a housing cavity with a spool assembly disposed within the housing cavity. The spool assembly is coupled with the gear assembly that controls a direction of rotation of the spool assembly. A first strap extends between a first end coupled with the first clamp assembly and a second end coupled with the spool assembly. A second strap extends between a third end coupled with the second clamp assembly and a fourth end coupled with the spool assembly. The lift housing moves in a first direction responsive to the spool assembly rotating in a first direction of rotation, and the lift housing moves in a second direction responsive to the spool assembly rotating in a second direction of rotation.
B66C 11/20 - Aménagements, p. ex. à pignons différentiels, permettant la manœuvre simultanée ou sélective de la translation ou du levageAménagements utilisant le même câble ou corde pour la translation et le levage, p. ex. dans les grues Temperley
B64F 5/50 - Manipulation ou transport des composants d'aéronefs
Systems, apparatuses, and methods provide for a tool to support components on a common hinge line axis. The tool includes a first pin and a second pin coupled in coaxial alignment with each other, defining the common hinge line axis. A first shouldered hinge pin is slidably disposed on the first pin and a second shouldered hinge pin is slidably disposed on the second pin. The first and second shouldered hinge pins allow translation along the common hinge line axis of the supported components when coupled to the first and second shouldered hinge pins. The first and second pins are disposed within a ball and socket joint, which enables pivotal adjustment of the common hinge line axis while maintaining the first and second pins co-axial to each other during adjustment of the common hinge line axis, to aid fit and assembly of the supported components to a mating structure.
The present disclosure provides a system for inspection of a surface of an aerodynamic structure in one aspect. The system includes a track overlapping with a section of the surface, one or more vehicles constrained to travel along the track, and one or more image sensors disposed on the one or more vehicles. The one or more image sensors are configured to acquire one or more images of the surface used to identify one or more predicted defects of the surface. The system further includes one or more tactile sensors disposed on the one or more vehicles. The one or more tactile sensors are configured to acquire dimensioning information for the one or more predicted defects.
Detecting foreign object debris (FOD) is provided. The method comprises receiving images captured by a number of imaging devices in a defined inspection area. A generative artificial intelligence (AI) model generates a natural language text caption describing the images. A text classifier AI model classifies FOD in the images based on the natural language text caption. An explainable AI model identifies words and phrases within the natural language text caption according to which the text classifier AI model made the classification. A report is displayed in a user interface, wherein for each identified FOD the report includes a location where the FOD was identified in the inspection area, the captured image with the natural language text caption, and highlighting of the key words and phrases identified by the explainable AI model. A generative AI translation model can then translate the report into a specified second language.
G06V 20/70 - Étiquetage du contenu de scène, p. ex. en tirant des représentations syntaxiques ou sémantiques
G06F 40/40 - Traitement ou traduction du langage naturel
G06T 11/60 - Édition de figures et de texteCombinaison de figures ou de texte
G06V 10/764 - Dispositions pour la reconnaissance ou la compréhension d’images ou de vidéos utilisant la reconnaissance de formes ou l’apprentissage automatique utilisant la classification, p. ex. des objets vidéo
G06V 20/40 - ScènesÉléments spécifiques à la scène dans le contenu vidéo
G06V 20/52 - Activités de surveillance ou de suivi, p. ex. pour la reconnaissance d’objets suspects
H04N 7/18 - Systèmes de télévision en circuit fermé [CCTV], c.-à-d. systèmes dans lesquels le signal vidéo n'est pas diffusé
H04N 23/695 - Commande de la direction de la caméra pour modifier le champ de vision, p. ex. par un panoramique, une inclinaison ou en fonction du suivi des objets
10.
METHODS OF CHARACTERIZING BONDLINE INTEGRITY OF STRUCTURAL ASSEMBLIES, METHODS OF ESTABLISHING REDUCED PROOF PRESSURES DIFFERENTIALS FOR PROOF TESTING A STRUCTURAL ASSEMBLY THAT INCLUDES A BONDLINE, METHODS OF PROOF TESTING A STRUCTURAL ASSEMBLY, AND ACOUSTIC EVALUATION SYSTEMS
Methods of characterizing bondline integrity of structural assemblies, methods of establishing reduced proof pressure differentials for proof testing a structural assembly that includes a bondline, methods of proof testing a structural assembly, and acoustic evaluation systems are disclosed herein.
The present disclosure relates to an FMS configured to accept a plurality of flight legs (beyond the standard five) for consideration when developing a flight plan. Allowing an FMS to receive a plurality of flight legs, beyond just five, is achieved by calculating a lateral trajectory and a vertical trajectory based on the current state of the flight path. This may be done mid-flight or initially when a given flight plan is entered by the pilot. The sequence of leg types that are entered may be used to generate a predicted final trajectory and output a GUI (graphical user interface) of the predicted final trajectory.
A composite joint inspection system and methods of use and forming are presented. A composite joint inspection system comprises a cavity formed by at least two composite components; a composite filler within the cavity; and a fiber optic cable running through the cavity extending out from at least one of a first end of the cavity or a second end of the cavity. The fiber optic cable is in contact with the composite filler.
An end effector configured to lift composite material through two different mechanisms and methods of picking and placing composite material are presented. The end effector comprises a vacuum end effector with a plurality of vacuum pogos configured to pick and place a composite preform in contact with the plurality of vacuum pogos, and an electrostatic membrane configured to be removably held by the plurality of vacuum pogos and pick and place a single ply composite material while the electrostatic membrane is held by the plurality of vacuum pogos.
A method for etching a substrate using a light emitting diode (LED) lamp includes placing the substrate in an etching chamber equipped with the LED lamp configured to emit ultra-violet (UV) having a selected wavelength. The method includes submerging the substrate in an electrolyte solution within the etching chamber and applying a bias voltage between the substrate and the electrolyte solution. The method includes illuminating the substrate with the UV light to irradiate the substrate's surface. The method includes removing the substrate from the electrolyte solution once a desired etch depth is achieved.
C25F 3/12 - Attaque de surface des matériaux semi-conducteurs
C25F 7/00 - Éléments de construction des cellules, ou leur assemblage, pour l'enlèvement électrolytique de matières d'objetsEntretien ou conduite
H01L 21/02 - Fabrication ou traitement des dispositifs à semi-conducteurs ou de leurs parties constitutives
H01L 21/67 - Appareils spécialement adaptés pour la manipulation des dispositifs à semi-conducteurs ou des dispositifs électriques à l'état solide pendant leur fabrication ou leur traitementAppareils spécialement adaptés pour la manipulation des plaquettes pendant la fabrication ou le traitement des dispositifs à semi-conducteurs ou des dispositifs électriques à l'état solide ou de leurs composants
15.
PORTABLE SYSTEMS AND METHODS FOR MONITORING MAINTENANCE EVENTS FOR AIRCRAFTS
A portable monitoring system and method includes a control unit having one or more processors that can access one or more technical specifications associated with a maintenance event of an aircraft. The maintenance event includes one or more steps that are to be completed by an operator to complete the maintenance event. The portable monitoring system includes one or more sensors that obtain data during the maintenance event of the aircraft. The data is associated with one or more actions of the operator and/or one or more characteristics of the aircraft during the maintenance event. The data includes two or more different types of modalities. The control unit monitors the maintenance event based in part on the data obtained by the sensors during the maintenance event and at least one of the technical specifications.
The present disclosure provides a thermal control apparatus. The thermal control apparatus includes an integrated circuit (IC) and a heater film arranged in thermal communication with the IC. The heater film is arranged to selectively heat the IC during relatively cold conditions, or rather, when a temperature associated with the IC reaches a threshold. The thermal control apparatus also includes a heatsink arranged in thermal communication with the IC for dissipating heat generated by the IC during relatively hot conditions.
Methods and apparatus for leakage identification are disclosed. A disclosed example apparatus to determine at least one of a presence of a leak or a characteristic of the leak corresponding to a target, includes a liquid sensor corresponding to the target, the liquid sensor including first and second electrodes, and a liquid transport material, wherein at least a portion of the liquid transport material is positioned between the first and second electrodes, and an inductor-capacitor resonance circuit electrically coupled to the first and second electrodes, the inductor-capacitor resonance circuit to measure a self-capacitance of the liquid sensor.
G01M 3/18 - Examen de l'étanchéité des structures ou ouvrages vis-à-vis d'un fluide par utilisation d'un fluide ou en faisant le vide par détection de la présence du fluide à l'emplacement de la fuite en utilisant des moyens de détection électrique pour tuyaux, câbles ou tubesExamen de l'étanchéité des structures ou ouvrages vis-à-vis d'un fluide par utilisation d'un fluide ou en faisant le vide par détection de la présence du fluide à l'emplacement de la fuite en utilisant des moyens de détection électrique pour raccords ou étanchéité de tuyauxExamen de l'étanchéité des structures ou ouvrages vis-à-vis d'un fluide par utilisation d'un fluide ou en faisant le vide par détection de la présence du fluide à l'emplacement de la fuite en utilisant des moyens de détection électrique pour soupapes
B64D 45/00 - Indicateurs ou dispositifs de protection d'aéronefs, non prévus ailleurs
A mounting assembly to support a thrust reverser that is mounted to an engine mount of an aircraft. The mounting assembly includes a support assembly configured to connect to the engine mount of the aircraft with the support assembly having a first lateral side and a second lateral side. A first arm is connected to the first lateral side of the support assembly and is configured to connect to a first section of the thrust reverser. A second arm is connected to the second lateral side of the support assembly and configured to connect to a second section of the thrust reverser. The first arm and the second arm are pivotally connected to the support assembly to support the first section and the second section of the thrust reverser at different angular positions.
F02K 1/72 - Inversion du flux de la soufflante utilisant des volets inverseurs de poussée ou des portes montées sur le carter de la soufflante la partie arrière du carter de la soufflante étant mobile pour découvrir des ouvertures d'inversion de poussée dans le carter de la soufflante
Examples are disclosed that relate to a method for detecting ice accretion present on an aircraft. In one example, a depth signal indicating a depth of water and/or ice collected on a baseplate in a collection chamber of an aircraft ice detector is received from a depth sensor. A mass signal indicating a mass of the water and/or ice collected on the baseplate is received from a mass sensor. A volume of the water and/or ice collected on the baseplate is calculated based on the depth signal and dimensions of the baseplate. A density of the water and/or ice collected on the baseplate is calculated based on the mass signal and the calculated volume of the water and/or ice collected on the baseplate. An ice accretion signal is output based on the calculated density of the water and/or ice collected on the baseplate being less than a threshold density.
A monument assembly for a vehicle and method for attaching a monument assembly to an aircraft. The monument assembly is capable of being a heavily loaded interior monument enclosure for an aircraft that includes a load bearing structural frame to be attached to a floor of the aircraft. The monument assembly includes a plurality of support members connected together and a set of floor fittings connected to the plurality of support members. The set of floor fittings configured to be connected to the vehicle. A plurality of non-loadbearing panels is connected to the plurality of support members. A load path of the monument assembly is carried by the plurality of support members and not the plurality of panels.
Aircraft cargo compartment airflow distribution system and aircraft cargo compartment airflow distribution sub-assemblies configured to modify a primary aircraft compartment airflow distribution assembly and methods are presently disclosed.
B64D 13/06 - Aménagements ou adaptations des appareils de conditionnement d'air pour équipages d'aéronefs, passagers ou pour emplacements réservés au fret l'air étant climatisé
22.
SYSTEM AND METHOD FOR REMOVING PAINT FROM A SUBSTRATE
A method includes applying a primer applied on a surface of a substrate, applying a nano-particle layer over the primer, and applying a paint layer over the nano-particle layer. The method for removing the paint layer from the substrate includes emitting signals, by an energy source, into the substrate, exciting a nano-particle layer by the signals, generating heat by the nano-particle layer in response to said exciting, and removing the paint layer by the heat.
C09D 5/00 - Compositions de revêtement, p. ex. peintures, vernis ou vernis-laques, caractérisées par leur nature physique ou par les effets produitsApprêts en pâte
Systems, methods, and apparatus for processing a signal using a non-uniform antenna array are disclosed. In one aspect, a receiver apparatus for processing high frequency signals is provided. The receiver apparatus may comprise an antenna array including a plurality of antenna elements. The plurality of antenna elements may include a first antenna element and a remainder of the plurality of antenna elements. The remainder of the plurality of antenna elements may be uniformly spaced apart from one another by a first distance and arranged in a substantially linear orientation. The remainder of the plurality of antenna elements may include a second antenna element spaced apart from the first antenna element by a second distance. The second distance may be different than the first distance.
G01S 3/46 - Systèmes pour déterminer une direction ou une déviation par rapport à une direction prédéterminée en utilisant des antennes espacées et en mesurant la différence de phase ou de temps entre les signaux venant de ces antennes, c.-à-d. systèmes à différence de parcours
24.
Vertical Air Vehicle Takeoff and Landing Stabilization Apparatuses, Systems, and Methods
Vertical takeoff and landing vehicles (VTOLs) of the type used for the point-to-point delivery and transport of payloads (e.g., packages, equipment, etc.) and personnel, are significantly stabilized at least during takeoff and landing with present aspects significantly ameliorating or significantly eliminating destabilizing effects, including ground effect, during VTOL takeoff and/or landing.
B64U 70/30 - Dispositions pour le lancement, le décollage ou l'atterrissage pour capturer en vol les véhicules aériens sans pilote via un dispositif d’arrêt terrestre ou maritime, p. ex. un câble ou un filet
B64U 101/64 - Véhicules aériens sans pilote spécialement adaptés à des utilisations ou à des applications spécifiques au transport de passagersVéhicules aériens sans pilote spécialement adaptés à des utilisations ou à des applications spécifiques au transport de marchandises autres que des armes à la livraison ou au retrait de colis
25.
Linkage Assembly Supporting a Material layer that Maintains a constant Length Across a Range of Motion
A reconfigurable structure includes one or more linkage assemblies that are each formed by one or more linkage chains of a plurality of linkages. Neighboring pairs of linkages of each linkage chain are rotatably coupled to each other via a first pin-in-slot joint and a second pin-in-slot joint. The reconfigurable structure includes a material layer mounted to the plurality of linkages of each linkage assembly. The material layer maintains a constant length across a range of motion of each linkage assembly, thereby reducing or eliminating in-plane strain of the material layer across the range of motion. In an example, the reconfigurable structure can provide a first configuration corresponding to an annular tube shape for a fluid vessel, conduit, or other suitable structure, and a second configuration corresponding to a flattened shape. The flattened shape of the second configuration can be used for storage and transport of the reconfigurable structure.
B60B 19/00 - Roues non prévues ailleurs ou ayant des caractéristiques précisées dans l'un des sous-groupes du présent groupe
B63B 1/28 - Caractéristiques hydrodynamiques ou hydrostatiques des coques ou des ailes portantes tirant une portance supplémentaire des forces hydrodynamiques du type ailes portantes à ailes portantes réglables
A reconfigurable structure includes one or more linkage assemblies that are each formed by one or more linkage chains of a plurality of linkages. Neighboring pairs of linkages of each linkage chain are rotatably coupled to each other via a first pin-in-slot joint and a second pin-in-slot joint. The reconfigurable structure includes a material layer mounted to the plurality of linkages of each linkage assembly. The material layer maintains a constant length across a range of motion of each linkage assembly, thereby reducing or eliminating in-plane strain of the material layer across the range of motion. In an example, the reconfigurable structure can provide a first configuration corresponding to an annular tube shape for a fluid vessel, conduit, or other suitable structure, and a second configuration corresponding to a flattened shape. The flattened shape of the second configuration can be used for storage and transport of the reconfigurable structure.
B60B 19/04 - Roues non prévues ailleurs ou ayant des caractéristiques précisées dans l'un des sous-groupes du présent groupe expansibles
B63B 1/28 - Caractéristiques hydrodynamiques ou hydrostatiques des coques ou des ailes portantes tirant une portance supplémentaire des forces hydrodynamiques du type ailes portantes à ailes portantes réglables
B64C 3/38 - Réglage des ailes complètes ou de certaines parties de ces ailes
Apparatuses and methods for shape-memory alloy elements and sensing. An aircraft assembly comprising a sensor, a cable connected to the sensor, and a shape-memory alloy (SMA) element connected to the cable. The SMA element is configured to change shape and control tension in the cable. A method of using an aircraft assembly by changing the shape of the SMA element by an amount corresponding to a change in a length of the cable.
B64D 45/00 - Indicateurs ou dispositifs de protection d'aéronefs, non prévus ailleurs
F03G 7/06 - Mécanismes produisant une puissance mécanique, non prévus ailleurs ou utilisant une source d'énergie non prévue ailleurs utilisant la dilatation ou la contraction des corps produites par le chauffage, le refroidissement, l'humidification, le séchage ou par des phénomènes similaires
G01B 5/00 - Dispositions pour la mesure caractérisées par l'utilisation de techniques mécaniques
Systems, apparatus, articles of manufacture, and methods are disclosed for a portable assembly jig including: a frame having a top side and a bottom side, the top side including structure to support an object, the bottom side defining at least three support locations to fully support the assembly jig in a parked condition, assembly of the object occurs in the parked condition; casters coupled to the frame enable movement of the frame in a portable condition; a jack coupled to at least one of the three support locations such that extension of a foot of the jack toward a ground surface causes at least one of the casters to be above the ground surface and the assembly jig to be in the parked condition; and at least one stabilizer foot coupled to the frame, a first stabilizer foot to stabilize the frame in the parked condition.
Systems, apparatus, articles of manufacture, and methods for corrosion detection are disclosed. An example apparatus includes an adhesive to removably couple the apparatus directly to a region of a substrate; a first sensor to measure a first parameter at the region; a second sensor to measure a second parameter at the region, the first parameter and the second parameter being factors of corrosion at the region; and a power supply to provide power to the first sensor and the second sensor.
A cryogenic tank support system and a method for installing a cryogenic tank on an aircraft. The cryogenic tank support system includes an inner ring of a support collar connected to an inner wall of a cryogenic tank. An outer ring of the support collar is connected to an outer wall of the cryogenic tank. The system also includes a saddle of a saddle bracket connected to the outer ring of the support collar. A mount surface of the saddle bracket is connected to a crown region of a fuselage of the aircraft. The system structurally isolates the cryogenic tank from the aircraft by carrying radial loads of the cryogenic tank and axial loads of the cryogenic tank with at least one support collar and carrying the radial loads of the cryogenic tank while allowing axial expansion/contraction of the cryogenic tank with at least one other support collar.
Aircraft cargo compartment airflow distribution system and aircraft cargo compartment airflow distribution sub-assemblies configured to modify a primary aircraft compartment airflow distribution assembly and methods are presently disclosed.
B64D 13/06 - Aménagements ou adaptations des appareils de conditionnement d'air pour équipages d'aéronefs, passagers ou pour emplacements réservés au fret l'air étant climatisé
32.
Using Artificial Intelligence to Generate 3D Artifacts and Model Based Definition from 2D Drawings
Generating a 3D model from 2D drawings is provided. The method comprises extracting, by a design parser, content from 2D engineering drawings of an assembly and comparing the extracted content to a bill of materials corresponding to a 3D computer assisted design (CAD) model of the assembly to identify missing components from the 3D CAD model. Responsive to identifying missing components, 3D representations of the missing components are modeled based on the 2D engineering drawings, and metadata and textual information related to the 2D engineering drawings. The 3D representations of the missing components are incorporated into the 3D CAD model of the assembly to create a complete 3D CAD model. A manufacturing process for the assembly is then controlled according to the complete 3D CAD model.
G06F 30/27 - Optimisation, vérification ou simulation de l’objet conçu utilisant l’apprentissage automatique, p. ex. l’intelligence artificielle, les réseaux neuronaux, les machines à support de vecteur [MSV] ou l’apprentissage d’un modèle
B29C 64/393 - Acquisition ou traitement de données pour la fabrication additive pour la commande ou la régulation de procédés de fabrication additive
B33Y 50/02 - Acquisition ou traitement de données pour la fabrication additive pour la commande ou la régulation de procédés de fabrication additive
G06F 30/15 - Conception de véhicules, d’aéronefs ou d’embarcations
Sequencing wire assembly for autonomous routing is described. Sequencing includes defining a weighted directed conflict graph representing a plurality of wires to be routed in a raceway includes a plurality of nodes defined by the plurality of wires and a plurality of edges defined by a set of routing precedents among the plurality of wires where a subsequent wire that is to be routed across a precedent wire within the raceway yields routing precedence to the precedent wire with regard to sequencing wire assembly denoted by one of the plurality of edges between the precedent wire and the subsequent wire that is directed from the precedent wire to the subsequent wire, increments an integer value of deg out=1 with regard to the precedent wire and increments an integer value deg in=1 with regard to the subsequent wire.
G01R 31/00 - Dispositions pour tester les propriétés électriquesDispositions pour la localisation des pannes électriquesDispositions pour tests électriques caractérisées par ce qui est testé, non prévues ailleurs
34.
SUPPORT ASSEMBLY FOR A FRAME STRUCTURE AND A METHOD OF SUPPORTING THE FRAME STRUCTURE
A support assembly and a method for a frame structure having a first frame section and a second frame section includes a support frame having arms extending outwardly to present a support grid. Connector apparatuses are arranged on the support grid, and each includes a lock coupled to a pin to selectively fix the pin in a stationary position relative to the support frame. Each of the connector apparatuses include a clamp configured to selectively attach together the frame structure and the support frame. The clamp of each of the connector apparatuses cooperates with the respective pin to attach the first frame section to the support frame when the respective clamp is in the locked position which fixes the first frame section on the support grid of the arms in an arrangement that provides repeatable nominal attachment and detachment of the second frame section relative to the first frame section.
Disclosed herein is a protective coating for a thermal protection ablator layer of a high-speed vehicle, the protective coating including a cured room-temperature-vulcanizing (RTV) silicone adhered to the thermal protection ablator layer through siloxane linkages, where the cured RTV silicone is formed from at least one organosilicon compound.
C09D 183/06 - Polysiloxanes contenant du silicium lié à des groupes contenant de l'oxygène
C08F 230/08 - Copolymères de composés contenant un ou plusieurs radicaux aliphatiques non saturés, chaque radical ne contenant qu'une seule liaison double carbone-carbone et contenant du phosphore, du sélénium, du tellure ou un métal contenant un métal contenant du silicium
Metal to composite joints and methods of forming are presented. A metal to composite joint for a platform comprises two metal structural components forming a portion of a first surface and a portion of a second surface of the metal to composite joint; and a dividing set of composite plies between the two metal structural components providing an escape path for volatiles between the two metal structural components.
A composite structure and methods of forming are presented. A composite structure comprises: structural supports and a structural skin formed by a plurality of composite panels fastened to the structural supports. Each composite panel of the plurality of composite panels comprises a first titanium end; a second titanium end; and a composite skin joined to and extending between the first titanium end and the second titanium end.
A cartridge mechanism for monitoring a clamping force of a temporary fastener includes an inner assembly, an outer assembly, and a displacement indicating system. The inner assembly has an inner cap and an inner spring. The outer assembly has an outer cap and an outer spring. The displacement indicating system indicates an amount of compressive displacement of the inner and outer springs that represents attainment of a preliminary clamping force exerted on the structure by the temporary fastener. The inner spring is uncalibrated and has a spring constant substantially equal to that of the outer spring, which is calibrated to one-half the preliminary clamping force at the amount of compressive displacement indicated by the displacement indicating system. The outer assembly is removable from the inner assembly to result in a final clamping force exerted by the temporary fastener on the structure of approximately one-half the preliminary clamping force.
A fastener installation assembly, an end-effector tool, and a method for installing fasteners into respective holes of a workpiece includes a container and retainer assemblies supported by the container. Each of the retainer assemblies include fingers configured to retain a respective one of the fasteners between the fingers in a pre-installed position. A first actuator is configured to move the respective fasteners to an installed position by ejecting the respective one of the fasteners out of the respective retainer assemblies and inserting the respective one of the fasteners into one of the holes of the workpiece. Each of the retainer assemblies include a compliance apparatus configured to allow the respective fasteners and the respective fingers to move independently of each other to self-align the respective fasteners with the respective one of the holes as the first actuator moves the respective fasteners from the pre-installed position to the installed position.
A computing system for aligning laser scan data is provided, including a processor configured to obtain multiple scan point sets, each set including a plurality of scan points that represent an outer surface of a target object. The processor is configured to generate a voxel map including an outer surface voxel layer for the target object, and compute a respective transformation matrix for each of the scan point sets. The processor is configured to apply the respective transformation matrix for each scan point set to the scan points in the respective scan point set to thereby transform a position of each of the scan points in each scan point set that lies partially or wholly outside of the outer surface voxel layer to a modified position within the outer surface voxel layer, to thereby generate respective transformed scan point sets containing the scan points at the modified positions.
An apparatus for monitoring structural health of an object includes a plurality of sensor pairs. The plurality of sensor pairs each includes an exciting sensor and a receiving sensor. The exciting sensor is configured to transmit a guided wave and the receiving sensor is configured to receive the guided wave. The plurality of sensor pairs are utilized to acquire an individual signature from each one to generate a plurality of individual signatures. A pseudo baseline signature is generated by computing an average of the plurality of individual signatures and compared to the individual signature of a corresponding one of the plurality of sensor pairs to determine whether the individual signature is different from the pseudo baseline signature. If the individual signature is different, an area of the object proximate to the corresponding one of the plurality of sensors pairs, is identified as a potential abnormality area.
A syntactic foam is comprised of a matrix, a quantity of porous polymer beads in the matrix, each of which is smaller than 1.5 mm in width, and a quantity of hollow microspheres distributed within the matrix amongst the quantity of porous polymer beads. The largest of the hollow microspheres is at least 7 times smaller than the smallest of the porous polymer beads, and the hollow microspheres have a size distribution of ±10 μm.
C08J 9/32 - Mise en œuvre de substances macromoléculaires pour produire des matériaux ou objets poreux ou alvéolairesLeur post-traitement à partir de compositions contenant des microbilles, p. ex. mousses syntactiques
B29C 67/20 - Techniques de façonnage non couvertes par les groupes , ou pour la fabrication d'objets poreux ou cellulaires, p. ex. des mousses plastiques, des mousses alvéolaires
B29C 67/24 - Techniques de façonnage non couvertes par les groupes , ou caractérisés par le choix de la matière
The present disclosure provides an adhesive applicator, an applicator system, and methods of applying an adhesive to a part. In one aspect, an applicator has an end effector that includes a roller wheel having a rotatable wheel and thermally-controlled tubes. The thermally-controlled tubes each define a chamber arranged to receive a heated working fluid. The end effector also includes leading rollers and lagging rollers that lead and lag the roller wheel, respectively. The leading and lagging rollers each define relief channels and are arranged to receive an adhesive substrate within their respective relief channels so as to pre-tension and align for placement of the adhesive substrate to a part to which the thermally-controlled tubes apply the adhesive substrate. The relief channels of the rollers along with controlled tensioning of the adhesive substrate and associated backing, maintain accurate placement of the adhesive substrate and removal of the backing during laydown.
B65H 37/02 - Appareils délivrant des articles ou des bandes, comportant des dispositifs pour exécuter des opérations auxiliaires particulières pour appliquer des adhésifs
B65H 35/00 - Délivrance d'articles à partir de machines à découper ou à perforer linéairementAppareils délivrant des articles ou des bandes, comportant des dispositifs pour couper ou perforer linéairement, p. ex. distributeurs de bande adhésive
44.
PRECIPITATION STATIC AIRCRAFT MODEL FOR ANTENNAS INTERFERENCE
A method is presented for evaluating precipitation static (p-static) radiofrequency interference. The method comprises receiving an aircraft surface model and generating a p-static charging model for the aircraft surface model. A charge state of the p-static charging model is adjusted based on a charge dissipation model. An emitted power spectra from the aircraft surface model is determined based on the adjusted charge state. Electrostatic emissions coupling to an antenna are determined based on the emitted power spectra. A level of p-static radiofrequency interference is indicated based on the electrostatic emissions coupling to the antenna.
A method is presented for discretizing an aircraft surface into p-static zones. The method comprises generating a particle impingement model for an aircraft surface using computational fluid dynamics. The particle impingement model is discretized to generate two or more p-static zones. P-static design guidelines are established on a per p-static zone basis. Unbonded conductive material and/or dielectric material is then applied to the aircraft surface based on the p-static design guidelines.
G06F 30/28 - Optimisation, vérification ou simulation de l’objet conçu utilisant la dynamique des fluides, p. ex. les équations de Navier-Stokes ou la dynamique des fluides numérique [DFN]
A composite fuselage section, including an outer skin comprising one or more composite materials, an internal framework to support the outer skin, and one or more mechanical fasteners disposed through the outer skin, wherein the internal framework is joined to the outer skin using the one or more mechanical fasteners, and wherein the outer skin includes a conductive layer surrounding at least one of the one or more mechanical fasteners to enhance an energy distribution of a lightning strike flowing across a surface of the composite fuselage section.
A hydraulic dissolved air measurement system and method are described that include a testing device, a pressure sensor, a piston actuation device, and a controller. The testing device includes a housing and a movable piston that define a measurement chamber configured to receive a hydraulic fluid sample from a hydraulic reservoir. The controller controls the piston actuation device to move the piston to expand the measurement chamber to an expanded state after the hydraulic fluid sample is received in the measurement chamber. The controller determines a volume change value that represents a volume increase of the measurement chamber based on the movement of the piston. The controller receives a pressure value from the pressure sensor that represents the pressure within the measurement chamber in the expanded state, and determines a dissolved air content of the hydraulic fluid sample based on the pressure value and the volume change value.
A method of modal testing a structure may include rigidly coupling a body of an inertial shaker to a structure under test, wherein the shaker has a rodless inertial mass enclosed in a housing and a voice coil configured to move the inertial mass in alternating directions within the housing. The shaker is activated by applying an alternating current to the voice coil at a selected frequency, and the resulting vibration response is measured at various points on the structure under test.
A strut assembly, for coupling an engine to a wing of an aircraft, includes a mid truss assembly including a fore portion and an aft portion. The strut assembly includes an engine mount member connected to the fore portion of the mid truss assembly and including a ring shape configured to fully encircle a portion of the engine when the strut assembly is connected to the engine. The strut assembly includes an aft truss assembly including a fore portion and an aft portion. The fore portion of the aft truss assembly is connected to the aft portion of the mid truss assembly. The strut assembly includes an aft strut bulkhead connected to the aft portion of the aft truss assembly. The strut assembly includes a wing mounting feature operatively connected to, and located aft of, the aft strut bulkhead. The strut assembly includes a plurality of engine mounting features.
Systems and methods for cooling an aircraft galley cart compartment by providing cooling from a potable water flow circuit directed from an aircraft potable water supply to provide direct and indirect cooling are disclosed.
B64D 13/06 - Aménagements ou adaptations des appareils de conditionnement d'air pour équipages d'aéronefs, passagers ou pour emplacements réservés au fret l'air étant climatisé
An apparatus for testing a cryogenic coupling includes a frame, a first clamp plate, and a second clamp plate. The first clamp plate is coupled to the frame and is configured to contact a first end of the cryogenic coupling. The second clamp plate is coupled to the frame and is configured to contact a second end of the cryogenic coupling. At least one of the first clamp plate and the second clamp plate is movable along the frame relative to one another such that the cryogenic coupling is clamped between the first clamp plate and the second clamp plate.
Methods and apparatus to evaluate the smoothness of a surface are disclosed. An example apparatus comprises interface circuitry, machine-readable instructions, and at least one processor circuit to be programmed by the machine-readable instructions to access a computer-generated model of a surface of an object to be evaluated for smoothness, segment the surface into a plurality of regions, each of the regions adjacent to or overlapping at least another one of the regions, select one of the regions to be evaluated for smoothness, measure a plurality of coordinates on the surface of the object corresponding to respective locations within the selected region, determine a reference surface based on the measured coordinates, compare the coordinates to the reference surface, and determine a smoothness parameter of the selected region based on the comparisons.
A computerized system configured to execute a multi-agent machine learning model for controlling a plurality of vehicles in a multi-vehicle autonomous control session in a multi-vehicle environment is disclosed. Multi-modal neural network agents of the model each control a corresponding autonomous vehicle in the session. The agents receive image data and parameter data, input the image data to an image feature extractor to produce an image feature vector, input the parameter data to a parameter data feature extractor to produce a parameter data feature vector, produce a joint latent representation of the image data and parameter data, and input the joint latent representation to an actor model neural network, to generate a selected action for the autonomous vehicle. The multi-agent machine learning model is configured to control each autonomous vehicle in the session according to the corresponding selected action for each autonomous vehicle.
G05D 1/243 - Moyens de capture de signaux provenant naturellement de l’environnement, p. ex. signaux optiques, acoustiques, gravitationnels ou magnétiques ambiants
G05D 101/15 - Détails des architectures logicielles ou matérielles utilisées pour la commande de la position utilisant des techniques d’intelligence artificielle [IA] utilisant l’apprentissage automatique, p. ex. les réseaux neuronaux
G05D 105/35 - Applications spécifiques des véhicules commandés pour le combat
A method for tracking a binary offset carrier (BOC) pseudo random noise (PRN) signal is disclosed. A BOC PRN signal is received from a satellite. A BOC PRN correlation between the BOC PRN signal and a local replica of the BOC PRN signal is formed. A center peak is extracted from the BOC PRN correlation. A center peak local replica signal is generated based on the center peak extracted from the BOC PRN correlation. A center peak correlation between the BOC PRN signal and the center peak local replica signal is formed. Navigation data for the satellite is retrieved from the BOC PRN signal based at least on the center peak correlation meeting steady tracking criteria.
Systems, apparatuses, and methods provide for looping through a plurality of airplane system alert types. An alert rule associated with individual airplane system alert types is determined, where the alert rule has an alert threshold associated with a category type. An airplane log datastore is scanned for error events associated with the alert rule. The error events are grouped based at least in part on the category type. A determination is made as to whether a group of error events meets the alert threshold. The group of error events is ignored in response to the alert threshold not being met.
B64F 5/60 - Test ou inspection des composants ou des systèmes d'aéronefs
G07C 5/08 - Enregistrement ou indication de données de marche autres que le temps de circulation, de fonctionnement, d'arrêt ou d'attente, avec ou sans enregistrement des temps de circulation, de fonctionnement, d'arrêt ou d'attente
H04L 9/32 - Dispositions pour les communications secrètes ou protégéesProtocoles réseaux de sécurité comprenant des moyens pour vérifier l'identité ou l'autorisation d'un utilisateur du système
A method of synchronizing files includes partitioning, based on a template, a first file into a first file portion and partitioning based on the template a second file into a second portion. The method further includes comparing a first value associated with the first portion with a second value associated with the second portion. The method further includes updating the first portion or the second portion based on the comparison.
A projectile includes a shell defining a cavity and one or more retainers. A bolo is disposed within the cavity and a backplate is engaged with the one or more retainers. The backplate is configured to separate from the shell to release the bolo in response to imbalanced forces resulting from deploying the projectile.
A system and a method include an alignment strip coupled to a surface. A vehicle is configured to move over the surface. The vehicle includes an ultraviolet (UV) light emitter configured to emit UV light onto the alignment strip. The UV light emitted by the UV light emitter illuminates the alignment strip. An imaging device is configured to acquire one or more images of the alignment strip as illuminated by the UV light.
G05D 1/244 - Dispositions pour déterminer la position ou l’orientation utilisant des aides à la navigation passive extérieures au véhicule, p. ex. marqueurs, réflecteurs ou moyens magnétiques
G05D 107/70 - Sites industriels, p. ex. entrepôts ou usines
A vehicle includes a body, a first microphone positioned in an interior of the body and configured to receive sound generated by movement of a first surface of the body relative to a fluid, and one or more processors coupled to the first microphone. The one or more processors are configured to receive an audio signal corresponding to sound received by the first microphone, analyze the audio signal to determine a first speed associated with the vehicle based on an acoustic signature associated with the first surface, and based at least on the speed of the vehicle, cause performance of one or more vehicle management operations.
H04R 1/40 - Dispositions pour obtenir la fréquence désirée ou les caractéristiques directionnelles pour obtenir la caractéristique directionnelle désirée uniquement en combinant plusieurs transducteurs identiques
A method for repairing a composite structure for electromagnetic effects (EME) protection, including identifying a repair area on a composite structure, applying a composite repair patch over the repair area, and applying a conductive layer over the composite repair patch and an area of the composite structure surrounding the composite repair patch, wherein the conductive layer overlaps the composite repair patch, wherein the conductive layer includes a metal or metal alloy, and wherein the conductive layer creates a conductive bridge over the composite repair patch to provide an EME protection to the composite structure and enhance a dispersion of lightning strike energy along the composite structure.
B29C 73/10 - Réparation d'articles faits de matières plastiques ou de substances à l'état plastique, p. ex. d'objets façonnés ou fabriqués par utilisation de techniques couvertes par la présente sous-classe ou la sous-classe utilisant des éléments préformés utilisant des pastilles d'obturation appliquées à la surface de l'objet
09 - Appareils et instruments scientifiques et électriques
12 - Véhicules; appareils de locomotion par terre, par air ou par eau; parties de véhicules
25 - Vêtements; chaussures; chapellerie
28 - Jeux, jouets, articles de sport
37 - Services de construction; extraction minière; installation et réparation
41 - Éducation, divertissements, activités sportives et culturelles
42 - Services scientifiques, technologiques et industriels, recherche et conception
Produits et services
Downloadable computer game software; Pre-recorded video discs, video recording and video tapes featuring information about aircraft, aircraft parts, aviation, avionics, aerospace products, and maintenance, operation, repair and training associated with aircraft and aerospace products, parts, and support equipment; Computer programs, downloadable, for viewing information about aircraft, aircraft parts, aviation, avionics, and maintenance, operation, repair and training associated with aircraft, aircraft parts, aviation, avionics, and support equipment Airplanes; Structural parts for airplanes; Airplanes and structural parts therefor T-shirts; Sweatshirts; Polo shirts; Hats; Sports caps and hats Toy models; Scale model airplanes; Scale model kits; Model planes Providing information relating to aircraft repair and maintenance; Aircraft maintenance or repair; Information with relation to aircraft construction, repair and maintenance; Technical support services, namely, technical advice related to the repair of mechanical operation, maintenance, and modification of aircraft Educational services, namely, conducting conducting classes, seminars, and conferences in the field of the operation, maintenance, repair, overhaul, and modification of aircraft and aircraft parts and distribution of training materials in connection therewith. Technology advisory services related to operation of computerized and software systems on aircraft; Aircraft design; Engineering design services in the field of aeronautics, aviation, and aircraft design
62.
PANEL ASSEMBLY FOR CONVERTING PASSENGER AIRCRAFT TO CARGO AIRCRAFT
A panel assembly for an aircraft can include a composite material skin with a cargo opening sized to receive cargo into the fuselage of the aircraft and to remove the cargo from the fuselage of the aircraft. The panel assembly can include curved panel edge frames coupled with the outer skin and disposed on opposite lateral sides of the cargo opening in the outer skin. Upper and lower sill beams can be disposed on opposite upper and lower sides of the cargo opening in the outer skin. The upper and lower sill beams each can be coupled with the panel edge frames. The upper and lower sill beams can be coupled with curved aircraft frames that are disposed inside the fuselage of the aircraft to secure the outer skin to the aircraft at a panel opening in the fuselage of the aircraft.
There is provided an automated fastener system having an automated washer installation. The automated fastener system includes an automated washer feed system holding and dispensing one or more washers, and providing a selected washer for the automated washer installation. The automated fastener system further includes an automated fastener holder assembly holding and dispensing one or more fasteners, and providing a selected fastener for the automated washer installation; an automated shuttle assembly; an automated inspection system; an automated delivery system; an automated installation system; and a control system. The automated washer installation is performed at one or more of, before inspection of the selected fastener, after inspection of the selected fastener, or after delivery of the selected fastener and the selected washer by the automated delivery system to the automated installation system.
B23P 19/08 - Machines pour placer des rondelles, bagues annulaires élastiques ou éléments analogues sur des boulons ou autres éléments
B23P 19/00 - Machines effectuant simplement l'assemblage ou la séparation de pièces ou d'objets métalliques entre eux ou des pièces métalliques avec des pièces non métalliques, que cela entraîne ou non une certaine déformationOutils ou dispositifs à cet effet dans la mesure où ils ne sont pas prévus dans d'autres classes
B25J 15/08 - Têtes de préhension avec des éléments en forme de doigts
B64F 5/10 - Fabrication ou assemblage d’aéronefs, p. ex. gabarits à cet effet
F16B 43/00 - Rondelles ou dispositifs équivalentsAutres dispositifs de support pour têtes de boulons ou d'écrous
64.
TRAY TABLES COMPRISING PLANT FIBERS AND METHODS FOR MANUFACTURING TRAY TABLES COMPRISING PLANT FIBERS
Beijing Aircraft Technology Research Institute (BATRI) of COMAC, Ltd. (Chine)
Inventeur(s)
Lin, Jun
Li, Xiaoling
Wang, Zhao
Shengcheng, Ji
Jiang, Xin
Dongsheng, Li
Abrégé
The disclosure relates to a method for manufacturing a tray table containing plant fiber and a tray table made therefrom. The manufacturing method comprises: a) homogenizing a halogen-free flame retardant to obtain a homogeneous halogen-free flame retardant; b) melting a thermoplastic resin and uniformly blending the molten thermoplastic resin with a plant fiber, the homogeneous halogen-free flame retardant, and a compatibilizer to obtain a plant fiber composite material; c) extruding and granulating the plant fiber composite material to obtain a granular composite material; and d) mixing the granular composite material with a foaming agent and injection molding to obtain the tray table. The tray table manufactured according to the method herein is green and environmentally friendly, non-toxic and harmless, and also has high flame-retardant effect and weight reduction effect.
B64D 11/06 - Aménagements ou adaptations des sièges
B29C 44/04 - Moulage par pression interne engendrée dans la matière, p. ex. par gonflage ou par moussage pour la fabrication d'objets de longueur définie, c.-à-d. d'objets séparés formés d'au moins deux parties en matière chimiquement ou physiquement différente, p. ex. ayant des densités différentes
B29C 45/00 - Moulage par injection, c.-à-d. en forçant un volume déterminé de matière à mouler par une buse d'injection dans un moule ferméAppareils à cet effet
The stanchion for an aircraft includes a first composite body defining a first channel having a first web extending between a first pair of spaced apart flanges. The first composite body also includes a first multitude of longitudinal segments each having a ply count that varies between adjacent longitudinal segments of the first multitude of longitudinal segments. The stanchion also includes a second composite body defining a second channel having a second web extending between a second pair of flanges. The second composite body also includes a second multitude of longitudinal segments each having a ply that varies between adjacent longitudinal segments of the second plurality of longitudinal segments with the first composite body being fixed relative to the second composite body.
Beam directors comprise a first mirror surface configured to be selectively rotated about a rotation axis, a second mirror surface facing the first mirror surface and configured to be selectively rotated about the rotation axis independent of rotation of the first mirror surface, and an electromagnetic radiation (EMR) device configured to emit or detect EMR along the rotation axis toward or from the first mirror surface. The first mirror surface and the second mirror surface are angled relative to the rotation axis so that at a plurality of rotational positions of the first mirror surface relative to the second mirror surface, the EMR directed along the rotation axis bounces off the first mirror surface and the second mirror surface.
G02B 26/12 - Systèmes de balayage utilisant des miroirs à facettes multiples
G02B 26/08 - Dispositifs ou dispositions optiques pour la commande de la lumière utilisant des éléments optiques mobiles ou déformables pour commander la direction de la lumière
67.
SHUTTER APPARATUS FOR USE IN A PART-MANUFACTURING PROCESS AND ASSOCIATED SYSTEM AND METHOD
A shutter apparatus for use in a part-manufacturing process is disclosed. The shutter apparatus includes a platen having a plurality of substrate locations. The shutter apparatus also includes a shutter defining a substrate-location aperture. The shutter covers the platen except for a selectable one of the plurality of substrate locations of the platen exposed through the substrate-location aperture. The substrate-location aperture is sized to expose only one of the plurality of substrate locations at a time, such that the shutter covers all but a selected one of the plurality of substrate locations. The shutter and the platen are selectively rotatable, relative to each other, to alternatingly expose a different selected one of the plurality of substrate locations.
Lightning swept stroke simulator devices comprise a first dielectric structure defining a first elongate slit, a second dielectric structure defining a second elongate slit, and an electrode positioned relative to the first dielectric structure and the second dielectric structure and configured to be operatively coupled to a voltage source. The first dielectric structure and the second dielectric structure are configured to be selectively moved relative to each other so that the first elongate slit and the second elongate slit overlap and collectively define an aperture that extends through the first dielectric structure and the second dielectric structure and that translates linearly along the first dielectric structure and the second dielectric structure.
A method comprises pressing a tool into a main-portion of a composite radius filler. Another method comprises changing a shape of at least a first main-portion surface of a main-portion of a composite radius filler by pressing a first tool surface of a tool into the first main-portion surface. A system comprises a tool and a composite radius filler comprising a body having a longitudinal axis. The body comprises a main-portion and an end-portion. The main-portion extends along the longitudinal axis and has a first stiffness. The body further comprises an end-portion that extends along the longitudinal axis, that is adjacent to the main-portion, and that has a second stiffness that differs from the first stiffness. At least a first portion of an interface between the main-portion and the end-portion is at an angle relative to the longitudinal axis.
A mechanism for moving a slat of an aircraft wing of an aircraft includes a rib, an arm, a first bar and a second bar. The arm is disposed generally parallel with the rib. The rib, the arm and the first and second bars cooperate to form a four-bar linkage. The first and second bars rotatable about connection points in a negative pitch rotational direction to dispose the arm in an extended position, and in a positive pitch rotational direction to dispose the arm in a default position.
A detection system for detecting net zero power communications. The detection system comprises a black body system with a cooled cavity, a radiation detector, and a controller. The radiation detector is configured to detect black body radiation. The controller is in communication with the radiation detector. The controller is configured to determine whether the black body radiation detected by the radiation detector has a pattern encoding information. The controller is configured to decode the information in the black body radiation in response to detecting the pattern.
H04B 10/69 - Dispositions électriques dans le récepteur
H04B 10/118 - Dispositions spécifiques à la transmission en espace libre, c.-à-d. dans l’air ou le vide spécialement adaptées aux communications par satellite
A computing system on an aircraft that is configured to perform operations including receiving historical data. The operations also include training a model using the historical data to produce a trained model. The operations also include receiving current pre-landing data for a current aircraft that is to land on a runway. The operations also include determining, during a time period before landing, a feasibility of a plurality of taxi exits on the runway based at least partially upon the trained model and the current pre-landing data. The operations also include selecting one of the taxi exits based at least partially upon the feasibility.
Network optimization for arranging computational sub-tasks in a hybrid-computing environment is provided. The method comprises receiving input of a network of nodes and edges representing computational processes and their constituent information, wherein the nodes are grouped according to whether the nodes use classical computing resources or quantum computing resources. The method generates workflow constraints, scheduling constraints and computing resource assignment constraints. The method generates an objective function. An optimization problem is solved according to the objective function and all said constraints. The solution determines a best computational objective achieved, a selected computational workflow through the nodes, compute job scheduling, and assignment of the computational processes among the classical computing resources and quantum computing resources. The computational workflow is then executed to achieve the best computational objective according to the computed job scheduling and assignment of computational processes among the classical computing resources and quantum computing resources.
G06F 9/48 - Lancement de programmes Commutation de programmes, p. ex. par interruption
G06F 9/50 - Allocation de ressources, p. ex. de l'unité centrale de traitement [UCT]
G06N 10/80 - Programmation quantique, p. ex. interfaces, langages ou boîtes à outils de développement logiciel pour la création ou la manipulation de programmes capables de fonctionner sur des ordinateurs quantiquesPlate-formes pour la simulation ou l’accès aux ordinateurs quantiques, p. ex. informatique quantique en nuage
74.
REAL-TIME GENERATION OF UNIQUE IDENTIFIERS FOR FLIGHT OBJECTS
The present disclosure provides a method comprising receiving, from a first data source, information for a flight object comprising a first set of fields and corresponding values that describe a first flight. The method further comprises retrieving global identifier record(s) from a database. Each global identifier record comprises a unique global identifier for a respective flight and a respective second set of fields and corresponding values of the database that describe the respective flight. The method further comprises calculating, based on a comparison of the first set with some or all of the respective second set(s), a respective confidence value for each pairing of the flight object with a respective one of the global identifier record(s). The method further comprises updating, when a calculated confidence value exceeds a threshold value, the global identifier record corresponding to the calculated confidence value using information from the first set.
Composite radius fillers and assemblies comprising composite radius fillers are disclosed. An example of a composite radius filler comprises a body having a longitudinal axis. The body comprises a main-portion and an end-portion. The main-portion extends along the longitudinal axis and has a first stiffness. The body further comprises an end-portion that extends along the longitudinal axis, that is adjacent to the main-portion, that defines at least a portion of a terminal end of the body, and that has a second stiffness that differs from the first stiffness. At least a first portion of an interface between the main-portion and the end-portion is at an angle relative to the longitudinal axis. Methods for a composite manufacturing method comprise constructing a composite radius filler. Aircraft assemblies comprising a composite radius filler are further disclosed.
One example provides a computing device comprising a display device, a logic subsystem, and a memory subsystem. The memory subsystem comprises instructions that are executable by the logic subsystem to display a graphical airspace representing an airspace on the display device, and obtain one or more notice to air missions (NOTAMs) related to the airspace. The instructions are further executable to, for each NOTAM of the one or more NOTAMs, display a graphic overlay on the graphical airspace. The graphic overlay has an appearance based at least upon a determined status of the NOTAM.
Generating data enriched voxels is provided. The method comprises receiving image data of a three-dimensional (3D) object. A number of key vertices are detected within the 3D object, and a bill of materials (BOM) is created for each key vertex. The BOM for each key vertex is then enriched with production data and sensor data, wherein the enriched BOM for each key vertex describes environmental conditions within a defined area around the 3D object. The enriched BOM for each key vertex are then fed into a respective neural network that generates a two-dimensional (2D) pixel containing all data from the enriched BOM, wherein the 2D pixel forms part of a tensor of 2D pixels.
G06F 30/12 - CAO géométrique caractérisée par des moyens d’entrée spécialement adaptés à la CAO, p. ex. interfaces utilisateur graphiques [UIG] spécialement adaptées à la CAO
79.
Radio Frequency Communications Using Laser Optical Breakdowns
A method, apparatus, and system for transmitting data. A radio frequency communications system comprising a computer system and a communications manager in the computer system. The communications manager is configured to identify data for transmission using radio frequency noise signals or other electromagnetic spectrum. The communications manager is configured to control an emission of laser beams at a set of optical breakdown points to cause optical breakdowns that generate radio frequency noise signals encoding the data.
A strongback is within the internal cabin of an aircraft. A first stowage bin is configured to couple to the strongback. The first stowage bin has a first size and a first shape. A second stowage bin is also configured to couple to the strongback. The second stowage bin has a second size and a second shape. One or both of the first size differs from the second size, or the first shape differs from the second shape. The strongback is configured to interchangeably receive and retain the first stowage bin and a second stowage bin.
An insulated wire includes a core body comprising electrically-conductive material. The insulated wire also includes a permanent coating comprising electrically-insulating material and disposed on the core body to electrically insulate the core body. The insulated wire further includes a removable coating disposed on the permanent coating to provide the core body and the permanent coating with structural support during cutting of the core body and the permanent coating to the desired length.
H01B 13/00 - Appareils ou procédés spécialement adaptés à la fabrication de conducteurs ou câbles
H01B 3/08 - Isolateurs ou corps isolants caractérisés par le matériau isolantEmploi de matériaux spécifiés pour leurs propriétés isolantes ou diélectriques composés principalement de substances inorganiques quartzIsolateurs ou corps isolants caractérisés par le matériau isolantEmploi de matériaux spécifiés pour leurs propriétés isolantes ou diélectriques composés principalement de substances inorganiques verreIsolateurs ou corps isolants caractérisés par le matériau isolantEmploi de matériaux spécifiés pour leurs propriétés isolantes ou diélectriques composés principalement de substances inorganiques laine de verreIsolateurs ou corps isolants caractérisés par le matériau isolantEmploi de matériaux spécifiés pour leurs propriétés isolantes ou diélectriques composés principalement de substances inorganiques laine de laitierIsolateurs ou corps isolants caractérisés par le matériau isolantEmploi de matériaux spécifiés pour leurs propriétés isolantes ou diélectriques composés principalement de substances inorganiques émaux vitreux
H01B 3/42 - Isolateurs ou corps isolants caractérisés par le matériau isolantEmploi de matériaux spécifiés pour leurs propriétés isolantes ou diélectriques composés principalement de substances organiques matières plastiquesIsolateurs ou corps isolants caractérisés par le matériau isolantEmploi de matériaux spécifiés pour leurs propriétés isolantes ou diélectriques composés principalement de substances organiques résinesIsolateurs ou corps isolants caractérisés par le matériau isolantEmploi de matériaux spécifiés pour leurs propriétés isolantes ou diélectriques composés principalement de substances organiques cires polyestersIsolateurs ou corps isolants caractérisés par le matériau isolantEmploi de matériaux spécifiés pour leurs propriétés isolantes ou diélectriques composés principalement de substances organiques matières plastiquesIsolateurs ou corps isolants caractérisés par le matériau isolantEmploi de matériaux spécifiés pour leurs propriétés isolantes ou diélectriques composés principalement de substances organiques résinesIsolateurs ou corps isolants caractérisés par le matériau isolantEmploi de matériaux spécifiés pour leurs propriétés isolantes ou diélectriques composés principalement de substances organiques cires polyéthersIsolateurs ou corps isolants caractérisés par le matériau isolantEmploi de matériaux spécifiés pour leurs propriétés isolantes ou diélectriques composés principalement de substances organiques matières plastiquesIsolateurs ou corps isolants caractérisés par le matériau isolantEmploi de matériaux spécifiés pour leurs propriétés isolantes ou diélectriques composés principalement de substances organiques résinesIsolateurs ou corps isolants caractérisés par le matériau isolantEmploi de matériaux spécifiés pour leurs propriétés isolantes ou diélectriques composés principalement de substances organiques cires polyacétals
H01B 7/18 - Protection contre les dommages provoqués par des facteurs extérieurs, p. ex. gaines ou armatures par l'usure, la contrainte mécanique ou la pression
H01B 7/38 - Conducteurs ou câbles isolés caractérisés par la forme avec des dispositions pour faciliter l'enlèvement de l'isolation
82.
MEASURING APPARATUS FOR ANGULARLY ADJUSTABLE SUPPORT TOOL INDEXES AND RELATED METHODS
A measuring apparatus for measuring an angularly adjustable indexing component includes a support fixture having a datum flange, and at least one displacement indicator. An indexing surface of the angularly adjustable indexing component is axially adjustable relative to the datum flange, and at least two holes extend through the datum flange. The displacement indicator is positioned through one hole to determine a first pivotal displacement of a surface of a part that is clamped against the indexing surface, relative to a nominal position of the part. The displacement indicator is then positioned through a different hole to determine a second pivotal displacement of the part surface at a second location. The measured first and second pivotal displacements enable determination of an axial orientation of the indexing surface relative to the nominal position of the part.
A method and a handling system for imparting a desired longitudinal conformation into a longitudinal component are presented. The handling system comprises a rigid frame and a plurality of handling headers movably connected to the rigid frame. The plurality of handling headers is configured to grip a longitudinal component, lift the longitudinal component, and cooperatively move to impart the desired longitudinal conformation into the longitudinal component.
Disclosed herein is a hoist tool including a hoist frame and a base structure. The hoist frame includes a structural framework having a first end and a second end and at least one first rotation-enabling coupling at the second end of the structural framework. The base structure includes at least one second rotation-enabling coupling configured to engage with the at least one first rotation-enabling coupling of the hoist frame. The at least one second rotation-enabling coupling of the base structure defines a rolling axis. The hoist frame is selectively movable by the hoist to position the at least one first rotation-enabling coupling into engagement with the at least one second rotation-enabling coupling and when coupled and when the assembled structure is coupled to the hoist frame, the hoist frame is selectively rotatable about the rolling axis, relative to the base structure, to enable a rollover of the assembled structure.
An environmental control system pack for an aircraft that includes a ram air circuit and a bleed flow circuit. The ram air circuit receives air from an atmosphere on an exterior of the aircraft and expels the air through an outlet back into the atmosphere. The bleed flow circuit receives bleed air and cools the air prior to the bleed air being delivered to an interior space. The environmental control system pack uses energy from the bleed air to drive a fan in the ram air circuit. This causes an increase in a compression power of the air in the ram air circuit to increase a thrust of the air exiting the ram air circuit through the outlet.
B64D 13/08 - Aménagements ou adaptations des appareils de conditionnement d'air pour équipages d'aéronefs, passagers ou pour emplacements réservés au fret l'air étant climatisé l'air étant réchauffé ou refroidi
B64D 13/06 - Aménagements ou adaptations des appareils de conditionnement d'air pour équipages d'aéronefs, passagers ou pour emplacements réservés au fret l'air étant climatisé
B64D 27/10 - Aéronefs caractérisés par le type ou la position des groupes moteurs du type à turbine à gaz
86.
SYSTEMS AND METHODS FOR DETECTING AN ANGLE OF AN AIRFLOW
A sensor includes an emitter electrode at a first position and exposed to a fluid airflow. The emitter electrode generates charged particles proximate the emitter electrode. The sensor includes an array of collector electrodes at a second position and exposed to the fluid airflow. Each collector electrode of the array of collector electrodes detects a current associated with an electric field of the charged particles during relative movement of the fluid airflow. The array of collector electrodes includes a first collector electrode aligned with the emitter electrode at a reference position, a first set of collector electrodes angularly offset from the first collector electrode in a first direction, and a second set of collector electrodes angularly offset from the first collector electrode in a second direction. Outputs from the array of collector electrodes indicate an angular direction of the relative movement of the fluid airflow.
B64D 43/02 - Aménagements ou adaptations des instruments pour indiquer la vitesse des aéronefs ou les conditions de décrochage
G01P 5/08 - Mesure de la vitesse des fluides, p. ex. d'un courant atmosphériqueMesure de la vitesse de corps, p. ex. navires, aéronefs, par rapport à des fluides en mesurant la variation d'une variable électrique directement affectée par l'écoulement, p. ex. en utilisant un effet dynamo-électrique
Semi-generative artificial intelligence modelling between domains is provided. The method comprises receiving a source image of an object in a first domain and diffusing the source image through a source diffusion model to generate a first Gaussian distribution in the first domain. Embeddings are generated from metadata which provides constraints for image reconstruction. The embeddings are fed into dual diffusion implicit bridges. The first Gaussian distribution is sampled and mapped, through the dual diffusion implicit bridges, from the first Gaussian distribution to a second Gaussian distribution in a second domain. The second Gaussian distribution is then reversed diffused through a target diffusion model to generate a target image of the object in the second domain in accordance with the metadata.
G06V 10/80 - Fusion, c.-à-d. combinaison des données de diverses sources au niveau du capteur, du prétraitement, de l’extraction des caractéristiques ou de la classification
A processing system and a method for manufacturing a component includes a workpiece having a work surface and an end-effector tool. The end-effector tool includes a fixture, and a set of first process tools attached to the fixture in a predetermined pattern. The first process tools are configured to perform a task to the work surface. The processing system also includes a controller in communication with the end-effector tool. The controller is configured to control movement of the end-effector tool to position the first process tools relative to the work surface such that the predetermined pattern is aligned at a predetermined location relative to the work surface. The controller is also configured to control operation of the first process tools such that the first process tools perform the task to the work surface to form a first processed area at the predetermined location of the work surface.
A twist-lock fastener includes an anchor and a retainer. The anchor is configured for attaching to a first article. The anchor includes a body forming a cavity. The retainer includes a locking portion and a holding portion. The locking portion is configured for inserting in the cavity and selectively locking to the body. The holding portion extends from the locking portion and is configured for holding a second article.
F16B 21/04 - Dispositifs de fixation largables verrouillant par rotation à baïonnette
F16B 2/26 - Clips, c.-à-d. dispositifs de fixation à serrage effectué uniquement par la résistance à la déformation inhérente au matériau dont est fait le dispositif en matériau non élastique pliable, p. ex. des ligatures pour plantes
90.
ANGULARLY ADJUSTABLE SUPPORT TOOL INDEXES AND RELATED METHODS
Methods of using an angularly adjustable support tool index for aligning a tool relative to a hole of a part with an index component having an indexing face being positioned against the part, include pivoting a trapped ball and socket joint with respect to a support fixture, which adjusts the index component to align with and support the part. A bushing couples the index component to the ball and socket joint, and a retaining lock secures the bushing in place with respect to the support fixture. The retaining lock restricts or prevents movement the ball and socket joint from movement and maintains a set position of the index component when the retaining lock is engaged with a shoulder of the bushing, and allows adjustment of the index component with respect to the support fixture when the retaining lock is selectively translated away from the bushing shoulder.
A sandwich panel has a first face sheet and a second face sheet, at least one of which is non-planar. In addition, the sandwich panel has a panel infill structure comprising an array of unit cell structures arranged in at least one layer connecting the first face sheet to the second face sheet. Each unit cell structure has a main axis that is locally normal to an imaginary mid-surface located midway between the first face sheet and the second face sheet. The panel infill structure has a consistent topology at each interface location where a unit cell structure is connected to the first face sheet or the second face sheet.
G06F 30/23 - Optimisation, vérification ou simulation de l’objet conçu utilisant les méthodes des éléments finis [MEF] ou les méthodes à différences finies [MDF]
B33Y 50/02 - Acquisition ou traitement de données pour la fabrication additive pour la commande ou la régulation de procédés de fabrication additive
B33Y 80/00 - Produits obtenus par fabrication additive
Methods comprise removing a to-be-elevated floorboard of an aircraft floor to create a void; following the removing, operatively placing an aircraft floorboard riser in engagement with floorboards adjacent to the void; and following the operatively placing the aircraft floorboard riser, operatively placing the to-be-elevated floorboard atop the aircraft floorboard riser.
An example tool-support apparatus includes a frame having a first support member, a second support member, a third support member, and a fourth support member; a first host-mating plate affixed to the first support member; a second host-mating plate affixed to the second support member; a first stabilizer affixed to the third support member; a second stabilizer affixed to the fourth support member; a first rail extending between the first support member and the third support member; a second rail extending between the second support member and the fourth support member; and a tool support member having a first end slidably coupled to the first rail and having a second end slidably coupled to the second rail.
A method for determining local variations in a surface of a fabricated component includes comparing surface scan data for the fabricated component represented in a first XYZ coordinate system to surface design data for the surface of the fabricated component, determining deviation data values for the surface based on the comparing, wherein the deviation data values are represented as deviation data points, selecting a first data point and neighboring data points from the deviation data points, determining an average normal vector for the first data point based on normal vectors of the first data point and the neighboring data points, defining an XY plane of a second XYZ coordinate system perpendicular to the average normal vector for the first data point, and projecting the first data point and the neighboring data points from the first XYZ coordinate system onto the XY plane of the second XYZ coordinate system.
G06F 30/20 - Optimisation, vérification ou simulation de l’objet conçu
G01B 11/00 - Dispositions pour la mesure caractérisées par l'utilisation de techniques optiques
G01B 11/30 - Dispositions pour la mesure caractérisées par l'utilisation de techniques optiques pour mesurer la rugosité ou l'irrégularité des surfaces
G06F 30/15 - Conception de véhicules, d’aéronefs ou d’embarcations
G06F 30/17 - Conception mécanique paramétrique ou variationnelle
G06F 119/02 - Analyse de fiabilité ou optimisation de fiabilitéAnalyse de défaillance, p. ex. performance dans le pire scénario, analyse du mode de défaillance et de ses effets [FMEA]
Disclosed herein is a hoist tool and associated system and method. The hoist tool includes a plurality of structure-attachment elements, each having a sleeve with an external annular groove, and configured to be attached to an assembled structure within an assembly jig at distinct locations. The hoist tool also includes a hoist frame. The hoist frame includes a structural framework, a plurality of jig-attachment features on the structure framework, and a plurality of clamping devices having opposing blade features that are configured to removably clamp to the external annular groove of a corresponding one of the plurality of structure-attachment elements. The hoist frame is configured to be removably coupled to the assembly jig, via the plurality of jig-attachment features and removably coupled to the assembled structure, via the plurality of clamping devices. When the hoist frame is removably coupled to the assembly jig and the assembled structure it is inhibited from imparting load to the assembled structure.
Systems and methods for manufacturing composite parts may include preheating a tool having a base made of a first material having a first coefficient of thermal expansion and a tooling surface made of a second material having a second coefficient of thermal expansion. Preheating includes heating the tooling surface at a first rate using a first heating system and heating the base at a second rate using a second heating system. Differences in dimensional growth due to thermal expansion of the base and the tooling surface are compensated by spaced-apart box structures coupling the tooling surface to the base, each of the box structures being made of the second material and having a first end fastened to the base and a second end fastened to a back side of the tooling surface.
B29C 70/44 - Façonnage ou imprégnation par compression pour la fabrication d'objets de longueur définie, c.-à-d. d'objets distincts utilisant une pression isostatique, p. ex. moulage par différence de pression, avec un sac à vide, dans un autoclave ou avec un caoutchouc expansible
B29C 33/04 - Moules ou noyauxLeurs détails ou accessoires comportant des moyens incorporés de chauffage ou de refroidissement utilisant des liquides, des gaz ou de la vapeur d'eau
B29C 33/06 - Moules ou noyauxLeurs détails ou accessoires comportant des moyens incorporés de chauffage ou de refroidissement utilisant des rayonnements
There is provided an automated fastener system having fastener conductivity testing. The automated fastener system has an automated fastener holder assembly holding fastener(s); an automated fastener shuttle assembly having shuttle cup(s); an automated fastener inspection system having an inspection center shaft, and inspection gripper fingers; an automated delivery system having a delivery device; an automated fastener installation system having an end effector with an end effector center shaft, and end effector gripper fingers; an automated eddy current conductivity probe system; and a processing system. The eddy current conductivity probe system has an eddy current conductivity probe assembly integrated in one of, the one or more shuttle cups, the inspection center shaft, the inspection gripper fingers, the end effector center shaft, or the end effector gripper fingers. The eddy current conductivity probe assembly contacts a selected fastener to perform the fastener conductivity testing, and to obtain an electrical conductivity measurement.
B23P 19/00 - Machines effectuant simplement l'assemblage ou la séparation de pièces ou d'objets métalliques entre eux ou des pièces métalliques avec des pièces non métalliques, que cela entraîne ou non une certaine déformationOutils ou dispositifs à cet effet dans la mesure où ils ne sont pas prévus dans d'autres classes
B64F 5/60 - Test ou inspection des composants ou des systèmes d'aéronefs
G01N 27/04 - Recherche ou analyse des matériaux par l'emploi de moyens électriques, électrochimiques ou magnétiques en recherchant l'impédance en recherchant la résistance
98.
SYSTEM AND METHOD FOR CLASSIFYING MAINTENANCE ISSUES FOR AIRCRAFT
A system and a method include a user interface including a display and an input device. The input device is configured for selection of one or more seed records regarding one or more maintenance issues of one or more vehicles. The user interface is further configured to output one or more first electronic signals that include the one or more seed records. A records database includes maintenance records for the one or more vehicles. A similarity engine control unit is in communication with the user interface and the records database. The similarity engine control unit is configured to receive the one or more first electronic signals including the one or more seed records, search the maintenance records within the records database, and find one or more return records including a subset of the maintenance records that are similar to the one or more seed records.
A door stop apparatus for limiting opening movement of a hinge mounted door is disclosed. The door stop apparatus may comprise a body member comprising a first end surface and a second end surface opposite and parallel to the first end surface. The body member may also comprise a through-opening extending between the first end surface and the second end surface, wherein the through-opening is configured to receive the hinge pin of the door hinge. Further, the body member may comprise an abutment surface extending between the first end surface and the second end surface, wherein the abutment surface is configured to abut against the door hinge for maintaining the body member in a substantially fixed position relative to the door hinge. Additionally, the body member may comprise a first side surface extending between the first end surface and the second end surface.
E05C 17/00 - Dispositifs pour tenir les battants dans une position d'ouvertureDispositifs pour limiter l'ouverture des battants ou pour tenir les battants dans une position d'ouverture par une pièce mobile disposée entre le battant et le dormantDispositifs de freinage, butées ou tampons combinés avec ces dispositifs
100.
METHODS FOR MANUFACTURING ADDITIVELY MANUFACTURED STRUCTURES FOR INTERNAL COMBUSTION ENGINES AND SAID ADDITIVELY MANUFACTURED STRUCTURES
A method for manufacturing an additively manufactured structure for an internal combustion engine includes identifying a start point on a build plate for construction of the additively manufactured structure and identifying an orientation of the additively manufactured structure to the build plate such that surface areas of the internal body surface and each internal port surface are at least approximately 20 degrees offset from parallel to the build plate for the additively manufactured structure such that no portion of the surface areas is equivalent to an area of a circle having a radius of 5 mm or larger. The additively manufactured structure includes a body member and at least two gas ports. The body member defines an external body surface and a body bore. The body bore defines an internal body surface. Each gas port defines an external port surface and a port bore. Each port bore defines an internal port surface.
