Disclosed herein is a method and a tooling assembly for manufacturing a composite part by forming a dry carbon fiber preform, employing a combination of a mold (102, 104), mandrels (110, 112, 113, 114, 115) and elastomeric bladders (116a, 116b) and injecting a resin into the mold.
B29C 33/40 - Matière plastique, p. ex. mousse ou caoutchouc
B29C 33/50 - Moules ou noyauxLeurs détails ou accessoires comportant des moyens ou conçus spécialement pour faciliter le démoulage d'objets, p. ex. des objets à contre-dépouille avec des moyens rétractables ou démontables élastiques
B29C 33/38 - Moules ou noyauxLeurs détails ou accessoires caractérisés par la matière ou le procédé de fabrication
2.
APPARATUS AND METHODS FOR FORMING COMPOSITE COMPONENTS
Herein is described a method of manufacturing a composite component (tool or part), wherein the method comprises: supplying resin (214) from a first port (220b) into a mould cavity (112); delaying supplying resin from a second port (220a, 220c) into the mould cavity until a resin front associated with the supply of resin from the first outlet reaches the second outlet; and supplying resin from the second outlet into the mould cavity once the resin associated with the supply of resin from the first outlet has reached the second outlet.
B29C 33/40 - Matière plastique, p. ex. mousse ou caoutchouc
B29C 33/50 - Moules ou noyauxLeurs détails ou accessoires comportant des moyens ou conçus spécialement pour faciliter le démoulage d'objets, p. ex. des objets à contre-dépouille avec des moyens rétractables ou démontables élastiques
B29C 33/38 - Moules ou noyauxLeurs détails ou accessoires caractérisés par la matière ou le procédé de fabrication
B29C 70/44 - Façonnage ou imprégnation par compression pour la fabrication d'objets de longueur définie, c.-à-d. d'objets distincts utilisant une pression isostatique, p. ex. moulage par différence de pression, avec un sac à vide, dans un autoclave ou avec un caoutchouc expansible
B29C 70/54 - Parties constitutives, détails ou accessoiresOpérations auxiliaires
3.
ELASTOMERIC TOOLING BLADDER AND ITS MANUFACTURING METHOD
A method of manufacturing an elastomeric tooling bladder (210, 310) is described. The method comprises: forming a first part (511) comprising a laminated composite material in a first mould (502), forming a second part (513) comprising a laminated material structure in a second mould (503), wherein the laminated composite material comprises a plurality of layers, and wherein at least one layer comprises a reinforced elastomer material; and joining the first part and the second part to form a bladder body defining a cavity (544), wherein the bladder body is configured to accommodate thermal expansion and contraction. Also described is an elastomeric tooling bladder.
B29C 33/40 - Matière plastique, p. ex. mousse ou caoutchouc
B29C 33/50 - Moules ou noyauxLeurs détails ou accessoires comportant des moyens ou conçus spécialement pour faciliter le démoulage d'objets, p. ex. des objets à contre-dépouille avec des moyens rétractables ou démontables élastiques
B29C 33/38 - Moules ou noyauxLeurs détails ou accessoires caractérisés par la matière ou le procédé de fabrication
4.
LIQUID SHIM FOR JOINTS AND METHODS OF CREATING AND APPLYING SAME
A liquid shim includes a bag (24) defining a closed inner volume and having sealed openings spaced inwardly from a periphery of the bag. The sealed openings are sealed from the closed inner volume and delimit holes extending through the bag. A liquid shim material (22) is flowable through the closed inner volume around the sealed openings and is curable to form a solid. The liquid shim material has a liquid shim material volume being less than the closed inner volume of the bag. A method of creating a liquid shim, and a method of shimming a gap between components, is also disclosed.
F16B 5/02 - Jonction de feuilles ou de plaques soit entre elles soit à des bandes ou barres parallèles à elles par organes de fixation utilisant un filetage
B64C 3/26 - Construction, forme ou fixation des revêtements distincts, p. ex. panneaux
B64F 5/10 - Fabrication ou assemblage d’aéronefs, p. ex. gabarits à cet effet
A material is formed by dividing a fabric into pieces that are substantially parallelogon in shape, the fabric having multiple parallel fibres. The pieces are placed, for example, with a pick and place machine, adjacent to each other on a carrier veil with fibres of adjacent of the pieces in substantial alignment. The pieces are attached to the carrier veil to form the material, the material including the pieces and the carrier veil.
B29C 70/38 - Empilage automatisé, p. ex. utilisant des robots, par application de filaments selon des modèles prédéterminés
B29C 70/54 - Parties constitutives, détails ou accessoiresOpérations auxiliaires
B29C 70/30 - Façonnage par empilage, c.-à-d. application de fibres, de bandes ou de feuilles larges sur un moule, un gabarit ou un noyauFaçonnage par pistolage, c.-à-d. pulvérisation de fibres sur un moule, un gabarit ou un noyau
B29C 70/08 - Façonnage de matières composites, c.-à-d. de matières plastiques comprenant des renforcements, des matières de remplissage ou des parties préformées, p. ex. des inserts comprenant uniquement des renforcements, p. ex. matières plastiques auto-renforçantes des renforcements fibreux uniquement comprenant des combinaisons de différentes formes de renforcements fibreux incorporés dans une matrice, formant une ou plusieurs couches, avec ou sans couches non renforcées
6.
NOISE-ATTENUATING DEVICE AND METHOD OF MANUFACTURE
Noise-attenuating devices, such as acoustic liners, and associated methods of manufacture are disclosed herein. The noise-attenuating devices have a perforated facing sheet with a coating applied thereto. The coating defines an exposed surface for direct exposure to the environment in which noise attenuation is desired. The coating also defines a flared entrance to one or more of the holes.
A variable area fan nozzle for a turbofan aircraft engine is described. The variable area fan nozzle comprises a first structure defining a forward portion of a bypass duct of the turbofan aircraft engine and a second structure defining an aft portion of the bypass duct. The second structure is movable relative to the first structure between a deployed position where a porting flow passage defined between the forward portion of the bypass duct and the aft portion of the bypass duct is open, and a stowed position where the porting flow passage is closed. The movable second structure comprises a vane and a slat attached to the vane and disposed forward of the vane. The porting flow passage extends between the slat and the vane when the second structure is in the deployed position.
F02K 1/09 - Variation de la section utile de la tubulure de jet ou de la tuyère par déplacement axial d'un organe externe, p. ex. d'un carénage
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
8.
RESIN BARRIER DEVICE, GASKET AND METHOD FOR INFUSING A PREFORM
Disclosed is a resin barrier device (1) for connection in a vacuum line, for use in resin infusion during composite manufacture. The resin barrier device includes a housing (3) having an inlet port (9) for connection to a resin source; and an outlet port (11) for connection to a vacuum source, and a flow path (13) extends between the inlet and outlet ports. A gas-permeable membrane (15) is disposed across the flow path (13) to prevent resin from flowing to the vacuum pump. Also disclosed is a gasket (17) for supporting the membrane (15), adapted to prevent resin leakage and a method of infusing a preform with a resin.
B29C 70/54 - Parties constitutives, détails ou accessoiresOpérations auxiliaires
B01D 29/05 - Filtres à éléments filtrants stationnaires pendant la filtration, p. ex. filtres à aspiration ou à pression, non couverts par les groupes Leurs éléments filtrants avec des éléments filtrants plats avec des supports
F16J 15/06 - Joints d'étanchéité entre surfaces immobiles entre elles avec garniture solide comprimée entre les surfaces à joindre
A nacelle for an aircraft having a thrust reverser including a translating cowl and a blocking panel. The blocking panel is connected by a pivot connection and is connected to the translating cowl by a sliding connection including an engagement member slidingly engaged in a track, the track having a first portion parallel to the longitudinal axis of the outer casing and a second portion non-parallel to the longitudinal axis. Motion of the translating cowl along the longitudinal axis slides the engagement member within the track, and is performed without moving the blocking panel when the engagement member is within the first portion of the track. The motion of the translating cowl causes the blocking panel to pivot about the pivot connection when the engagement member is within the second portion of the track.
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
Systems and methods to facilitate a steep final approach phase of flight of an aircraft are disclosed. In one embodiment, a method for operating an aircraft during a steep approach phase of flight of the aircraft comprises operating an engine of the aircraft at an idle speed associated with the steep approach type that is lower than an idle speed associated with a non-steep approach type capable of being executed by the aircraft. The method also comprises operating an ice protection system of the aircraft during the steep approach phase of flight of the aircraft.
G05D 1/06 - Régime de modification de l'altitude ou de la profondeur
B64D 15/16 - Dégivrage ou antigivre des surfaces externes des aéronefs par dispositifs mécaniques, p. ex. des gaines ou des bourrelets fixés ou incorporés à la surface et soumis à des pulsations
Ice protection systems of aircraft and related methods are disclosed. In one embodiment, the system comprises a gas-discharge lamp configured to emit infrared radiation toward an inner surface of an aircraft skin and an electric power source operatively connected to the gas-discharge lamp.
Assemblies and methods for facilitating the assembly of aircraft wings to a fuselage are disclosed. In some embodiments, a wing unit includes features that are configured to define one of more parts of a pressure vessel that is partially defined by the fuselage portion. In some embodiments, the aircraft assemblies disclosed herein comprise one or more first structural interfaces that permit positional adjustment between the wing unit and the fuselage portion so that one or more second structural interfaces may be finished only after such positional adjustment. In some embodiments, the aircraft assemblies disclosed herein comprise one or more structural interfaces that are disposed outside of the wing unit in order to eliminate or reduce the need for assembly personnel to access the interior of the wing unit to carry out the structural assembly of the wing unit to the fuselage portion.
Assemblies and methods for facilitating the assembly of aircraft wings to a fuselage are disclosed. In some embodiments, a wing unit includes features that are configured to define one of more parts of a pressure vessel that is partially defined by the fuselage portion. In some embodiments, the aircraft assemblies disclosed herein comprise one or more first structural interfaces that permit positional adjustment between the wing unit and the fuselage portion so that one or more second structural interfaces may be finished only after such positional adjustment. In some embodiments, the aircraft assemblies disclosed herein comprise one or more structural interfaces that are disposed outside of the wing unit in order to eliminate or reduce the need for assembly personnel to access the interior of the wing unit to carry out the structural assembly of the wing unit to the fuselage portion.
Test rigs and methods for performing functional tests on a cabin management system (CMS) of a passenger cabin of an aircraft or other mobile platform are disclosed. In some embodiments, a test rig comprises a plurality of components of the CMS functionally integrated in a manner representative of the installation of the components in the passenger cabin; and a framework supporting the functionally integrated components. The layout of the components on the framework is non-dimensionally representative of the installation of the components in the passenger cabin.
B64D 11/00 - Arrangements pour passagers ou équipageInstallations de postes de pilotage non prévues ailleurs
B64F 5/60 - Test ou inspection des composants ou des systèmes d'aéronefs
B64F 5/00 - Tracé, fabrication, assemblage, nettoyage, entretien ou réparation des aéronefs, non prévus ailleursManipulation, transport, test ou inspection de composants d’aéronefs, non prévus ailleurs
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
15.
TEMPERATURE CORRECTION OF VERTICAL SPEED OF AIRCRAFT
The present disclosure provides methods and systems for correcting a vertical speed of an aircraft. An instantaneous vertical speed of the aircraft is obtained, based on inertial data from an inertial reference unit on the aircraft. A first correction is applied to the instantaneous vertical speed to generate a baro-inertial vertical speed, and a second correction is applied to the baro-inertial vertical speed based on an error between a geometric vertical speed and the baro-inertial vertical speed to obtain a temperature- corrected baro-inertial vertical speed.
G01C 5/06 - Mesure des hauteursMesure des distances transversales par rapport à la ligne de viséeNivellement entre des points séparésNiveaux à lunette en utilisant des moyens barométriques
G01C 21/16 - NavigationInstruments de navigation non prévus dans les groupes en utilisant des mesures de la vitesse ou de l'accélération exécutées à bord de l'objet navigantNavigation à l'estime en intégrant l'accélération ou la vitesse, c.-à-d. navigation par inertie
G01P 3/62 - Dispositifs caractérisés par l'utilisation de la variation de la pression atmosphérique avec l'altitude pour mesurer la composante verticale de la vitesse
G05D 1/06 - Régime de modification de l'altitude ou de la profondeur
G08G 5/02 - Aides pour l'atterrissage automatique, c. à d. systèmes dans lesquels les données des vols d'avions arrivant sont traitées de façon à fournir les données d'atterrissage
G01C 23/00 - Instruments combinés indiquant plus d’une valeur de navigation, p. ex. pour l’aviationDispositifs de mesure combinés pour mesurer plusieurs variables du mouvement, p. ex. la distance, la vitesse ou l’accélération
Assemblies and methods for facilitating the assembly of aircraft wings to a fuselage are disclosed. In some embodiments, a wing unit includes features that are configured to define one of more parts of a pressure vessel that is partially defined by the fuselage portion. In some embodiments, the aircraft assemblies disclosed herein comprise one or more first structural interfaces that permit positional adjustment between the wing unit and the fuselage portion so that one or more second structural interfaces may be finished only after such positional adjustment. In some embodiments, the aircraft assemblies disclosed herein comprise one or more structural interfaces that are disposed outside of the wing unit in order to eliminate or reduce the need for assembly personnel to access the interior of the wing unit to carry out the structural assembly of the wing unit to the fuselage portion.
An insert for an air intake of a suction duct, the insert including an inner portion configured to extend within the suction duct, a mating portion configured for sealingly engaging the air intake, and an outer portion configured for extending outside of the suction duct. The inner portion includes a conduit having a central axis extending along an inlet direction at the inlet end and along an outlet direction at the outlet end, the inlet and outlet directions being non-parallel. The outlet end has a smaller cross-sectional area than that of the suction duct. The insert includes an inlet in fluid communication with the inlet end of the conduit. The outer portion includes a curved lip surrounding at least part of an inlet opening of the inlet, the lip configured to direct a flow into the inlet opening and toward the inlet end of the conduit.
Apparatus and methods for installing composite rivets are disclosed. One disclosed method comprises: inserting a composite rivet blank comprising a composite material into a hole in a part; heating the composite rivet blank using Joule heating while the composite rivet blank is in the hole; and then finishing the composite rivet blank.
B29C 65/08 - Assemblage d'éléments préformésAppareils à cet effet par chauffage, avec ou sans pressage avec des vibrations ultrasonores
B29C 65/36 - Assemblage d'éléments préformésAppareils à cet effet par chauffage, avec ou sans pressage avec des éléments chauffés qui restent dans le joint, p. ex. un "élément de soudage perdu" chauffés par induction
B29C 65/34 - Assemblage d'éléments préformésAppareils à cet effet par chauffage, avec ou sans pressage avec des éléments chauffés qui restent dans le joint, p. ex. un "élément de soudage perdu"
B21J 15/08 - Rivetage par application de chaleur aux extrémités des rivets afin de permettre la formation des têtes
B21J 15/14 - Machines à riveter spécialement adaptées au rivetage de pièces déterminées, p. ex. machines pour poser les garnitures de frein
B29C 65/18 - Assemblage d'éléments préformésAppareils à cet effet par chauffage, avec ou sans pressage avec un outil chauffé
B29C 65/72 - Assemblage d'éléments préformésAppareils à cet effet par des opérations combinées, p. ex. soudage et couture
19.
AIRCRAFT ELECTRICAL ISOLATION COMPONENT AND METHOD OF MANUFACTURING ELECTRICAL ISOLATION COMPONENT
A structural assembly of an aircraft has a fastener extending into first and second structural members. A washer (120) is disposed between the fastener and one of the structural members to electrically insulate the fastener and the structural members. The washer has a core (121) of reinforcement fibers supported in a thermoplastic matrix material (122). Electrically-insulating outer layers of glass fibers (124) overlay the core.
A hinge assembly for receiving a door, for example for an aircraft storage bin, and including a wall having opposed inner and outer surfaces, an edge of the wall including two spaced apart wall panels extending from a respective one of the inner and outer surfaces and defining part of a perimeter of an opening closable by the door; a pivot located between the wall panels, the pivot defining a pivot axis intersecting the wall panels; and a hinge arm having a portion received between the wall panels and engaged to the pivot, the hinge arm extending away from the wall panels and configured for attachment to the door, the hinge arm pivotable about the pivot axis to be movable between open and closed positions of the door, the hinge arm movable between the open and closed position within a plane extending between the opposed inner and outer surfaces.
Methods and systems relating to the design and testing of systems that include hinged flight control surfaces of aircraft are disclosed. The systems and methods disclosed herein make use of a structural model representing a structural environment of the system in a relatively simple manner. In various embodiments, the structural model comprises one or more actuation branches having a common linear actuation direction, a load mass, and a massless connector representative of a hinge line of the flight control surface. The massless connector is connected to and disposed between the one or more actuation branches and the load mass and is movable along the common linear actuation direction so that linear movement of the massless connector is correlated to rotational movement of the hinged flight control surface.
An assembly for connecting an engine to an aircraft, including a first support configured to be structurally connected to the engine, a second support configured to be structurally connected to the aircraft, and a thrust link. The thrust link includes a load transferring member having opposed ends each connected to a respective one of the supports for transferring engine thrust loads from the engine to the aircraft along a longitudinal axis of the load transferring member. The opposed ends have a fixed position relative to each other. The thrust link further includes a tuned absorber coupled to the load transferring member intermediate the opposed ends. The tuned absorber is tuned to absorb engine noise of at least one predetermined frequency. A thrust link and a method for reducing a transfer of noise generated by the engine to the aircraft are also discussed.
A slat (50) for an aircraft wing comprises a leading edge (51) defining a leading edge line (61), a trailing edge (52) defining a trailing edge line (62), the leading and trailing edges line defining a slat plane, the chord distance (69) extending normal to the leading edge and measured along the slat plane; an inboard edge extending between the leading and trailing edges; and an outboard edge (56) extending between the leading and trailing edges. The outboard edge comprises a first side portion having a projection on the plane defining a first side line (63), and a second side portion having a projection on the plane defining a second side line (64), the second side line being disposed at a first angle to the first side line and at a second angle to the leading edge line as it extends toward the inboard and trailing edges. A wing assembly and an aircraft including the slat are also disclosed.
A cushioning element for use in a vehicle, for example in an aircraft, includes at least one tuned absorber embedded within the cushioning element. The tuned absorber is tuned to absorb noise at a predetermined frequency of at least 20 Hz. A method of providing noise absorption within a cabin of a vehicle includes determining a predetermined frequency of at least 20 Hz of an undesirable noise within the cabin, and configuring an internal structure of a cushioning element to define a tuned absorber tuned to absorb noise at the predetermined frequency, the cushioning element in use being located in the cabin.
G10K 11/172 - Procédés ou dispositifs de protection contre le bruit ou les autres ondes acoustiques ou pour amortir ceux-ci, en général utilisant des effets de résonance
G10K 11/168 - Sélection de matériaux de plusieurs couches de matériaux différents, p. ex. sandwiches
25.
STORAGE CONTAINER AND BED PROVIDED WITH A STORAGE CONTAINER
A storage container (100) has a base (102) defining at least one storage compartment (202, 204, 206, 208, 210, 212), a top (104) movable between closed and opened positions, latching and locking assemblies. The latching assembly (500) has a latching actuator (110) movable between first and second positions. The latching assembly (500) locks the top (104) to the base (102) when the top (104) is in the closed position and the latching actuator (110) is in the first position and releases the top (104) from the base (102) when the latching actuator (110) is in the second position. The locking assembly has a lock actuator (801) having actuated and released positions. The top (104) is movable when the lock actuator (801) is in the actuated position. The locking assembly locking the top (104) in the open, closed, or an intermediate position when the lock actuator (801) is in the released position. The latching actuator (110) and the lock actuator (801) are operatively connected to the top (104) and move with the top (104) between the closed and the opened position.
The aircraft control systems and methods disclosed herein are configured to detect a residual error associated with a flight control computer of an aircraft and mitigate the effect(s) of such residual error in order to maintain safe operation of the aircraft. In some embodiments, the systems and methods are configured to detect an out-of-flight-envelope situation of the aircraft and determine whether or not the flight control computer is attempting to recover the aircraft from the out-of-flight-envelope situation. If the flight control computer is perceived as attempting to recover the aircraft from the out-of-flight-envelope situation, the flight control computer is permitted to continue controlling the aircraft. Otherwise, the excursion outside of the normal flight envelope is perceives as potentially having been caused by a residual error and the flight control computer is prevented from continuing to control the aircraft.
G05D 1/00 - Commande de la position, du cap, de l'altitude ou de l'attitude des véhicules terrestres, aquatiques, aériens ou spatiaux, p. ex. utilisant des pilotes automatiques
B64C 13/50 - Dispositifs de transmission avec amplification de puissance utilisant l'énergie électrique
G06F 11/16 - Détection ou correction d'erreur dans une donnée par redondance dans le matériel
The present disclosure provides an aircraft (10), as well as systems and methods for reducing current flow to electrical systems onboard an aircraft (10). A signal return network (220) is spaced from a composite structure (210) and first and second non-conductive components (240) are attached between the signal return network (220) and the composite structure (210) at first and second attachment points (242, 244), respectively. A conductive component (250) is attached between the signal return network (220) and the composite structure (210) at a third attachment point (246) for electrically coupling the signal return network (220) to the composite structure (210).
The present disclosure provides methods, systems, and apparatuses for controlling operation of a flight information recorder of an aircraft. A plurality of flight parameters, including a speed parameter, an engine operation parameter, an in-air parameter, and a descent parameter of the aircraft are monitored. When a shutdown condition associated with the flight parameters is satisfied, power to the flight information recorder is removed via an electrical system of the aircraft.
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
29.
METHOD FOR REPAIRING A COMPOSITE STRINGER WITH A COMPOSITE REPAIR CAP
Methods and composite repair caps (26) for repairing composite stringers (12) of structures (10) of mobile platforms are disclosed. In one exemplary embodiment, a stringer repair method includes overlaying a pre-cured composite repair cap on an outer surface (22) of the composite stringer so that the composite repair cap extends over a damaged portion (12A) of the composite stringer. The composite repair cap is then secured to the composite stringer to permit load transfer between the composite stringer and the composite repair cap.
B29C 73/04 - Réparation d'articles faits de matières plastiques ou de substances à l'état plastique, p. ex. d'objets façonnés ou fabriqués par utilisation de techniques couvertes par la présente sous-classe ou la sous-classe utilisant des éléments préformés
B29C 73/10 - 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
An assembly for securing a first component to a second component, including an attachment bracket having two openings defined therethrough, each of the openings having a closed perimeter, and a tie element extending through the openings, the tie element including two abutment portions each sized relative to the openings to prevent the abutment portions from passing through the openings, the abutment portions being positioned on opposite sides of one of the openings with at least one of the abutment portions being positioned between the openings. The components may be a harness and a fuel probe, for example in a fuel tank of an aircraft.
H02G 3/32 - Installations de câbles ou de lignes sur les murs, les sols ou les plafonds utilisant des colliers de fixation
F16L 3/233 - Supports pour tuyaux, pour câbles ou pour conduits de protection, p. ex. potences, pattes de fixation, attaches, brides, colliers spécialement adaptés pour supporter un certain nombre de tuyaux parallèles séparés par un espace pour un faisceau de tuyaux ou un ensemble de tuyaux disposés les uns à coté des autres en contact mutuel au moyen d'une bande flexible
31.
AUTOMATIC ARMING OF AIRCRAFT STEEP APPROACH FUNCTION
Systems and methods for automatically arming a steep approach function of an aircraft are disclosed. One exemplary method comprises automatically initiating arming of the steep approach function of the aircraft based on data (e.g., glide slope angle) associated with the approach procedure to be performed by the aircraft.
G08G 5/02 - Aides pour l'atterrissage automatique, c. à d. systèmes dans lesquels les données des vols d'avions arrivant sont traitées de façon à fournir les données d'atterrissage
G05D 1/06 - Régime de modification de l'altitude ou de la profondeur
The present disclosure provides methods and system for controlling the operation of an aircraft aileron which comprises an inboard portion and an outboard portion. A velocity of the aircraft is determined. Then, based on the velocity of the aircraft, the aileron is caused to move in certain ways. Below a first velocity threshold, the inboard aileron portion and the outboard aileron portion are caused to move substantially in unison. Between the first velocity threshold and a second, greater, velocity threshold, the outboard portion of the aileron is caused to lock and the inboard portion of the aileron is caused to move independently from the outboard portion. Above the second velocity threshold, the inboard portion is caused to move substantially opposite from the outboard portion.
Apparatus and method for conditioning engine-heated air onboard an aircraft including a heat exchanger (140) at least partially disposed in a pylon structure (118) for supporting an engine (134) of the aircraft. The pylon heat exchanger (140) extracts heat from a flow (156) of engine-heated air. A flow (142) of ambient air is provided to the pylon heat exchanger (140) from a ram air inlet (150).
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 15/04 - Dégivrage ou antigivre des surfaces externes des aéronefs par gaz chaud ou liquide amené par conduit par amenée de gaz chaud
B64D 33/00 - Aménagement sur les aéronefs des éléments ou des auxiliaires des ensembles fonctionnels de propulsion, non prévu ailleurs
B64D 27/26 - Aéronefs caractérisés par la structure du montage du groupe moteur
The present disclosure provides methods and system for controlling the operation of a fly- by-wire aircraft. One or more yaw commands are received from an operator control, and one or more actual induced rolls rates are determined based on the yaw commands. A yaw signal and a roll-countering command are sent to flight control components of the aircraft, the yaw signal to cause a yaw motion in the aircraft, and the roll-countering command to counter the actual induced rolls. A standardized roll rate command is determined based on the yaw command, and the standardized roll rate command is sent to the flight control components to cause a roll motion in the aircraft.
Ducts and methods for directing a flow of air from air-cooled devices onboard aircraft are disclosed. An exemplary method disclosed comprises: receiving air carrying heat extracted from the device, directing the air away from the device, and, discharging the air to at least one of an exterior of the aircraft and to an interior of the aircraft. A proportion of the air discharged to the exterior of the aircraft and to the interior of the aircraft is passively changed based on an operating condition such as the airspeed of the aircraft.
B64D 13/00 - Aménagements ou adaptations des appareils de conditionnement d'air pour équipages d'aéronefs, passagers ou pour emplacements réservés au fret
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
36.
PANELS FOR OBSTRUCTING AIR FLOW THROUGH APERTURES IN AN AIRCRAFT WING
Apparatus for improving flow characteristics around aircraft wings by obstructing air flow through an aperture formed in a wing skin for a movable duct or track are disclosed. In one embodiment, the apparatus comprises a substantially rigid panel movable at least partially across the aperture for at least partially occluding the aperture and for accommodating movement of a slat track extending through the aperture. In another embodiment, the apparatus comprises a hinged panel configured to swing outwardly from an outer side of the wing skin toward an open position to accommodate movement of an anti-icing duct extending through the aperture and to swing toward a closed position at least partially occluding the aperture.
An emergency exit assembly for an aircraft, including a window frame, a window assembly having an outer surface abutting the inner surface of the window frame around its perimeter, and retaining elements spaced around the perimeter of the window assembly. The retaining elements are each connected to the window frame and bias the window assembly toward and against the inner surface of the window frame. Each retaining element has a force-release portion so that the window assembly can be disengaged from the window frame through release of the force- release portion. The force-release portion may be a frangible portion breakable upon application of the pulling force. A cable with one or more handle(s) may be connected to the retaining elements to apply the pulling force. A method of accessing an emergency exit of an aircraft is also discussed.
The present disclosure describes displaying on a flight deck (12) graphical presentations indicative of performance limitations of an aircraft (10) resulting from an in-flight aircraft reconfiguration. The graphical presentations are co-located on the flight deck (12) with the graphical presentations of the aircraft (10) and/or system (34) parameters to which the performance limitations apply.
G01C 23/00 - Instruments combinés indiquant plus d’une valeur de navigation, p. ex. pour l’aviationDispositifs de mesure combinés pour mesurer plusieurs variables du mouvement, p. ex. la distance, la vitesse ou l’accélération
B64D 43/00 - Aménagements ou adaptations des instruments
G01D 1/00 - Dispositions pour la mesure donnant des résultats autres que la valeur instantanée d'une variable, d'application générale
G05D 1/00 - Commande de la position, du cap, de l'altitude ou de l'attitude des véhicules terrestres, aquatiques, aériens ou spatiaux, p. ex. utilisant des pilotes automatiques
A method of and a system for displaying an aircraft control input. The method comprises accessing a first indication indicative of an aircraft control input, the aircraft control input being associated with an orientation and an amplitude of the aircraft control input; generating, by a processing unit, a first single visual indication based on the first indication, the first single visual indication being reflective of the orientation and the amplitude of the aircraft control input; and causing the display of the first single visual indication on a display surface, the display of the first single visual indication providing a user viewing the first single visual indication with an understanding of the orientation and the amplitude of the aircraft control input.
Systems, devices and methods for alerting a crew of an aircraft or other mobile platform of a relevant condition associated with the aircraft are disclosed. One exemplary method comprises receiving data indicative of an existence of the relevant condition associated with the aircraft; receiving data indicative of a substantially real-time value of a dynamic parameter associated with the relevant condition; and displaying an awareness-enhancing indication associated with the relevant condition in a display area of the crew alerting system of the aircraft. The awareness-enhancing indication comprises a textual message and a supplemental indication indicative of the substantially real-time value of the dynamic parameter associated with the relevant condition. In various embodiments, the supplemental indication may be textual or graphical. The supplemental indication may also be indicative of a target value of the dynamic parameter.
Aircraft pitch control systems and methods are disclosed. An aircraft pitch control system (28) comprises a movable horizontal stabilizer (24) and an elevator (26) movably coupled to the horizontal stabilizer. The elevator is electronically geared to the horizontal stabilizer.
A floating bend radius device for limiting a radius of curvature of a flexible tube having a minimum bend radius, including first and second members. The first member has a curved contact surface having a radius of curvature at least equal to the minimum bend radius. The contact surface is concave in a plane transverse to the flexible tube's axial direction for contacting a portion of the flexible tube. The second member is engageable to the first member and complementary to the contact surface. The engaged members define a tube receiving space between the second member and the contact surface of the first member. The tube receiving space has a cross-sectional dimension configured to provide a compressive force on the flexible tube. At least one locking device may interconnect the members. A tube assembly including a bend radius device and a flexible tube is also discussed.
The disclosure discloses apparatus and methods for repairing defects such as porosity and/or edge delamination in composite laminates (14) by infusion of flowable matrix material (16). In some embodiments, methods disclosed herein comprise infusing the flowable matrix material (16) into a space in the composite laminate through the use of a formed hole (42) extending at least partially through the composite laminate (14). In some embodiments, methods disclosed herein comprise infusing the flowable matrix material (16) into a space in the composite laminate in a stepwise manner in order to obtain more complete filling of such space.
B29C 73/02 - Réparation d'articles faits de matières plastiques ou de substances à l'état plastique, p. ex. d'objets façonnés ou fabriqués par utilisation de techniques couvertes par la présente sous-classe ou la sous-classe utilisant un liquide ou un matériau pâteux
B29C 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
There is described a vehicle color-lighting control system. The system comprises at least one sidewall (101) having an electrically-controllable coloring mechanism (106) embedded therein and arranged for coloring at least a portion of the at least one sidewall with at least one first color; a lighting sub-system (110) comprising at least one light source (112) mounted within the vehicle to illuminate an interior of the vehicle with at least one second color in a first state and with at least one third color in a second state; and a controller coupled to the coloring mechanism and the lighting sub-system and configured for operating the coloring mechanism to color the at least one portion of the at least one sidewall with the at least one first color and concurrently illuminate the interior of the vehicle with the at least one second color.
B60Q 3/74 - Agencement des dispositifs d’éclairage pour l’intérieur des véhiculesDispositifs d’éclairage spécialement adaptés à l’intérieur des véhicules caractérisés par leur objet pour l’éclairage général de l’habitacleAgencement des dispositifs d’éclairage pour l’intérieur des véhiculesDispositifs d’éclairage spécialement adaptés à l’intérieur des véhicules caractérisés par leur objet pour l’éclairage général de l’habitacle en combinaison avec un éclairage spécifique, p. ex. des lampes d’habitacle avec des lampes de lecture
A preform tool (30) for shaping uncured composite material, including a central section having a mold surface (40) corresponding to a surface of the desired component shape, and at least a first side section (34) detachably connected to the central section and having a support surface extending as a continuation of the mold surface, and a cover (36). The junction between the mold and support surface is located along an edge of the desired component shape. The cover is movable between an engaged position in proximity of the mold surface for retaining the composite material, and a disengaged position located further away from the mold surface than in the engaged position. Also, a method of shaping composite material includes conforming composite plies to the mold surface, disengaging each side section from the central section and trimming the excess composite material extending laterally from the mold surface.
B29C 70/46 - Façonnage ou imprégnation par compression pour la fabrication d'objets de longueur définie, c.-à-d. d'objets distincts utilisant des moules opposables, p. ex. pour déformer des préimprégnés [SMC] ou des "prepregs"
B29C 70/54 - Parties constitutives, détails ou accessoiresOpérations auxiliaires
B29D 99/00 - Matière non prévue dans les autres groupes de la présente sous-classe
A blended wing body aircraft wherein at least each profile section corresponding to the normalized half-span values from 0 to 0.2 has a thickness ratio having a nominal value within the range set forth in Table 1. Also, a blended wing body aircraft wherein at least each profile section corresponding to the normalized half-span values from 0.15 to 0.3 has a normalized chord having a nominal value within the range set forth in Table 1, and wherein a ratio between a maximum thickness of the center body and the chord length along the centerline has a nominal value of at least 16%. Also, a blended wing body aircraft wherein a region of the aircraft defined by normalized half-span values from 0.1 to 0.2 has a normalized chord having a dimensionless rate of change from -3.5 to -5.1, and a thickness ratio having a rate of change from -0.27 to -0.72.
A blended wing body aircraft having an interior cabin with a usable volume of at most 4500 ft3 and a cabin aspect ratio of at most 4, wherein a combination of the wings and center body has a wetted aspect ratio of at least 1.7 and at most 2.8. Also, a blended wing body aircraft having an interior cabin with a usable volume of at least 1500 ft3 and at most 4500 ft3 and a cabin aspect ratio of at least 2 and at most 4, wherein a combination of the wings and center body has a wetted aspect ratio of at least 1.9 and at most 2.7. Also, a blended wing body aircraft wherein at least each profile section having normalized half-span values from 0 to 0.3 has a leading edge having a normalized height having a nominal value within the range set forth in Table 4.
The mobile platform cabin (20) disclosed herein comprises a passenger portion (22), a first cargo portion (24) disposed aft of the passenger portion (22), a partition (36) separating the passenger portion (22) from the first cargo portion (24), a second cargo portion (26) disposed aft of the first cargo portion (24) and a barrier net (38) separating the first cargo portion (24) from the second cargo portion (26). The first cargo portion (24) comprises a cargo-receiving zone (40) and a stay-out zone (44) in which cargo is not permitted. The barrier net (38) is configured to distend into the first cargo portion (24) when restraining forward movement of cargo (48) in the second cargo portion due to the cargo (48) in the second cargo portion being subjected to an acceleration relative to the cabin. At least part of the distension of the barrier net (38) is accommodated by the stay-out zone (44) of the first cargo portion (24).
Noise attenuating devices and methods, precursors and abrasive blasting masks for manufacturing noise attenuating devices are disclosed. An exemplary method disclosed herein comprises bonding a facing sheet (12) of the noise attenuating device (10) to a cellular core (14) and then perforating (18) the facing sheet. Perforating the facing sheet may be performed by abrasive blasting using a mask (26) configured to prevent the abrasive blasting of an underlying structure.
B64D 33/02 - Aménagement sur les aéronefs des éléments ou des auxiliaires des ensembles fonctionnels de propulsion, non prévu ailleurs des entrées d'air de combustion
B24C 1/04 - Méthodes d'utilisation de jet abrasif en vue d'effectuer un travail déterminéUtilisation d'équipements auxiliaires liés à ces méthodes pour travailler uniquement certaines parties déterminées, p. ex. pour graver la pierre ou le verre
G03F 7/00 - Production par voie photomécanique, p. ex. photolithographique, de surfaces texturées, p. ex. surfaces impriméesMatériaux à cet effet, p. ex. comportant des photoréservesAppareillages spécialement adaptés à cet effet
B32B 3/12 - Produits stratifiés comprenant une couche ayant des discontinuités ou des rugosités externes ou internes, ou une couche de forme non planeProduits stratifiés comprenant une couche ayant des particularités au niveau de sa forme caractérisés par une couche discontinue, c.-à-d. soit continue et percée de trous, soit réellement constituée d'éléments individuels caractérisés par une couche d'alvéoles disposées régulièrement, soit formant corps unique dans un tout, soit structurées individuellement ou par assemblage de bandes indépendantes, p. ex. structures en nids d'abeilles
B32B 7/12 - Liaison entre couches utilisant des adhésifs interposés ou des matériaux interposés ayant des propriétés adhésives
B32B 3/26 - Produits stratifiés comprenant une couche ayant des discontinuités ou des rugosités externes ou internes, ou une couche de forme non planeProduits stratifiés comprenant une couche ayant des particularités au niveau de sa forme caractérisés par une couche continue dont le périmètre de la section droite a une allure particulièreProduits stratifiés comprenant une couche ayant des discontinuités ou des rugosités externes ou internes, ou une couche de forme non planeProduits stratifiés comprenant une couche ayant des particularités au niveau de sa forme caractérisés par une couche comportant des cavités ou des vides internes
50.
SYSTEM FOR AND METHOD OF CONTROLLING FUNCTIONS IN A VEHICLE CABIN
A method of operation for a system incorporating a graphical user interface embedded in a knob disposed on a side ledge within a cabin of an aircraft includes displaying a menu for at least one controllable parameter, receiving a selection of the controllable parameter, displaying at least one control for the selected controllable parameter, receiving a control input for the selected controllable parameter, and adjusting the selected controllable parameter consistent with the control input. The controllable parameter comprises a plurality of controllable parameters selected from a group comprising light intensity, light color, temperature, media type, media content, media volume, and the degree of openness of at least one window shade. A knob and an executable computer program product also are provided.
G06F 3/0362 - Dispositifs de pointage déplacés ou positionnés par l'utilisateurLeurs accessoires avec détection des translations ou des rotations unidimensionnelles [1D] d’une partie agissante du dispositif de pointage, p. ex. molettes de défilement, curseurs, boutons, rouleaux ou bandes
51.
SYSTEM FOR AND METHOD OF CONTROLLING FUNCTIONS IN A VEHICLE CABIN
A distributed architecture for multi-nodal control of functions in an aircraft cabin. The distributed architecture includes a processor, a controller operatively connected to the processor, a passenger IO node operatively connected to the controller, and a crew IO node operatively connected to the controller. The passenger IO node and the crew IO node are capable of controlling at least one of light intensity in the aircraft cabin, color of light in the aircraft cabin, temperature in the vehicle cabin, and a degree of openness of one or more window shades in the aircraft cabin. A method and an executable computer program product also are provided.
G06F 3/0488 - Techniques d’interaction fondées sur les interfaces utilisateur graphiques [GUI] utilisant des caractéristiques spécifiques fournies par le périphérique d’entrée, p. ex. des fonctions commandées par la rotation d’une souris à deux capteurs, ou par la nature du périphérique d’entrée, p. ex. des gestes en fonction de la pression exercée enregistrée par une tablette numérique utilisant un écran tactile ou une tablette numérique, p. ex. entrée de commandes par des tracés gestuels
G06F 3/01 - Dispositions d'entrée ou dispositions d'entrée et de sortie combinées pour l'interaction entre l'utilisateur et le calculateur
G06F 3/0482 - Interaction avec des listes d’éléments sélectionnables, p. ex. des menus
52.
SYSTEM AND A METHOD OF OPERATION OF THE SYSTEM INCORPORATING A GRAPHICAL USER INTERFACE IN A BULKHEAD OF A VEHICLE CABIN
A method of operation for a system incorporating a graphical user interface disposed in a bulkhead within a cabin of an aircraft. The method includes displaying a menu for at least one controllable parameter, receiving a selection of the controllable parameter, displaying at least one control for the selected controllable parameter, receiving a control input for the selected controllable parameter, and adjusting the selected controllable parameter consistent with the control input. The controllable parameter may be one from a plurality of controllable parameters selected from a group that includes cabin light intensity, cabin light color, temperature, and the degree of openness of at least one window shade. A system and an executable computer program product also are provided.
G06F 3/0482 - Interaction avec des listes d’éléments sélectionnables, p. ex. des menus
G06F 3/0484 - Techniques d’interaction fondées sur les interfaces utilisateur graphiques [GUI] pour la commande de fonctions ou d’opérations spécifiques, p. ex. sélection ou transformation d’un objet, d’une image ou d’un élément de texte affiché, détermination d’une valeur de paramètre ou sélection d’une plage de valeurs
B64D 11/00 - Arrangements pour passagers ou équipageInstallations de postes de pilotage non prévues ailleurs
53.
SYSTEM AND A METHOD OF OPERATION OF THE SYSTEM INCORPORATING A GRAPHICAL USER INTERFACE ON A MOBILE COMPUTING DEVICE FOR A PASSENGER IN A VEHICLE CABIN
A method of operation for a system incorporating a graphical user interface in a mobile computing device for a passenger within a cabin of an aircraft. The method includes displaying a menu for at least one controllable parameter, receiving a selection of the controllable parameter, displaying at least one control for the selected controllable parameter, receiving a control input for the selected controllable parameter, and adjusting the selected controllable parameter consistent with the control input. The controllable parameter include a plurality of controllable parameters selected from a group encompassing light intensity, light color, temperature, and the degree of openness of at least one window shade. A system and executable computer program product also are provided.
G06F 3/0482 - Interaction avec des listes d’éléments sélectionnables, p. ex. des menus
G06F 3/0484 - Techniques d’interaction fondées sur les interfaces utilisateur graphiques [GUI] pour la commande de fonctions ou d’opérations spécifiques, p. ex. sélection ou transformation d’un objet, d’une image ou d’un élément de texte affiché, détermination d’une valeur de paramètre ou sélection d’une plage de valeurs
54.
SYSTEM AND METHOD FOR REPRESENTING A LOCATION OF A FAULT IN AN AIRCRAFT CABIN
A method and a distributed architecture for representing a location of a fault in an aircraft cabin, comprising: a controller operatively connected to a processor; a crew IO node operatively connected to the controller; the processor being configured to perform: detecting, by the controller, that an event of a system of the aircraft cabin corresponding to a fault has occurred; determining, by the processor, which aircraft cabin section amongst a plurality of aircraft cabin sections is associated with the system for which the event corresponding to the fault has occurred; and displaying, on the crew IO node, (i) a graphical user interface (GUI) component representing at least a portion of the aircraft cabin comprising at least some of the plurality of aircraft cabin sections and (ii) a visual indication identifying the aircraft cabin section associated with the system for which the event corresponding to the fault has occurred.
A grommet for surrounding a conduit received through a hole in a part, including a grommet body configured for engagement with a perimeter of the hole in the part and defining a closed or substantially closed perimeter, and a plurality fingers, the fingers extending axially from the grommet body and being circumferentially spaced from one another, each of the fingers being elongated and having a free end axially spaced from the grommet body. An assembly includes the part, the grommet, the conduit, and an adjustable length fastener spaced from the part, the adjustable length fastener forming a loop having an adjustable perimeter, the conduit and the fingers extending within the loop, the adjustable length fastener retaining the fingers against the outer surface of the conduit. A method of supporting a conduit within a hole through a part is also discussed.
F16L 5/00 - Dispositifs utilisés pour le passage des tuyaux, des câbles ou des conduits de protection au travers des murs ou des cloisons
F16L 3/20 - Supports pour tuyaux, pour câbles ou pour conduits de protection, p. ex. potences, pattes de fixation, attaches, brides, colliers avec disposition particulière permettant au tuyau de bouger permettant un mouvement latéral
Patches (20) and associated methods for repairing composite laminates (10) are disclosed where the composite laminate comprises a plurality of laminate plies (18) oriented according to a stacking sequence of the composite laminate and the patch comprises a plurality of repair plies (22) configured to at least partially fill a cavity (12) formed in the composite laminate and where the repair plies of the patch are oriented according to a stacking sequence different from the stacking sequence of the composite laminate.
B29C 73/10 - Réparation d'articles faits de matières plastiques ou de substances à l'état plastique, p. ex. d'objets façonnés ou fabriqués par utilisation de techniques couvertes par la présente sous-classe ou la sous-classe utilisant des éléments préformés utilisant des pastilles d'obturation appliquées à la surface de l'objet
B29L 31/30 - Véhicules, p. ex. bateaux ou avions, ou éléments de leur carrosserie
B64F 5/45 - Réparation de fuites dans les réservoirs de carburant
57.
METHOD AND APPARATUS FOR FORMING A COMPOSITE SKIN-STIFFENER ASSEMBLY
A method of forming a composite part (10) having a skin (12) and at least one elongated stiffener (14) extending from the skin (12), the method comprising: providing a mold (20) having a mold surface (22, 26) and a respective elongated compaction cavity for each stiffener (14), each compaction cavity (24) opening into the mold surface (22, 26); for each stiffener (14): placing a bagged insert (30) including an insert (40) received in a tubular bag (42) in the respective compaction cavity (24), supporting the stiffener (14) with the bagged insert (30), the stiffener (14) having a first part extending in the compaction cavity (24) snuggly between a side surface of the bagged insert (30) and an adjacent side surface of the mold (20) bordering the compaction cavity (24), the stiffener (14) having a second part connected to the first part and extending over at least one of the mold surface (22, 26) and a top surface of the bagged insert (30); placing a skin (12) over and in contact with the mold surface (22, 26), and over and in contact with the second part of each stiffener (14); forming a sealed enclosure containing the skin (12) and each stiffener (14), the sealed enclosure being formed in part by each tubular bag (42), each insert being located outside of the sealed enclosure; reducing a pressure within the sealed enclosure; removing each insert from the tubular bag (42); and curing the skin (12) and each stiffener (14). An insert assembly and an assembly for forming a composite part (10) are also discussed.
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 33/50 - Moules ou noyauxLeurs détails ou accessoires comportant des moyens ou conçus spécialement pour faciliter le démoulage d'objets, p. ex. des objets à contre-dépouille avec des moyens rétractables ou démontables élastiques
Class dividers for aircraft passenger cabins comprising pivoting luggage bins (20) are disclosed. The class divider comprises a curtain (24B) mounted inside the passenger cabin to extend into a space allotted for movement of the pivoting luggage bin. The curtain (24B) is resiliently deformable to accommodate the movement of the pivoting luggage bin (20).
Stringer-less fuselage structures and associated methods of manufacturing are disclosed. In some embodiments, a fuselage structure includes a composite fuselage skin (24) including a plurality of tear straps (32) formed in the composite fuselage skin where each tear strap extends generally along a longitudinal axis of the composite fuselage skin. The fuselage structure also includes a plurality of frames (28) supporting an interior of the composite fuselage skin where the frames are spaced apart along the longitudinal axis of the composite fuselage skin.
A method of and a system for presenting an operating status of an aircraft engine. The method comprises accessing a first indication indicative of a position of an aircraft engine start switch and accessing a second indication indicative of an aircraft engine start operating mode, the second indication having been generated based on an analysis of a parameter associated with an operating condition of the aircraft engine. The method, upon determining that the position of the aircraft engine start switch is an "on" position and the aircraft engine start operating mode is a healthy start causes the display of a visual indication indicative of the healthy start. The method upon determining that the position of the aircraft engine start switch is an "on" position and the aircraft engine start operating mode is an abnormal start causes the display of a visual indication indicative of the abnormal start.
A window system for an enclosure subjected to a change in air pressure, the enclosure having a window having an air-filled cavity, the system including a first path configured to allow air within the cavity of the window to vent out of the cavity, a second path configured to allow air to flow into the cavity, and a drying agent disposed within the second path, where moisture in the air entering the window cavity through the second path is reduced by the drying agent.
A method of repairing damage to a composite material (12) comprising a composite substrate (14) and at least one layer of shielding material (16). The method comprises the following steps: a) removing damage to the at least one layer of shielding material (16) by creating a hole (20) in the at least one layer of shielding material; b) applying a patch (28, 32) of shielding material in the region of the hole via a resin, wherein a ratio of a resin weight to a weight of the patch of shielding material lies in a range between about 0.45 - 0.55; and c) curing the resin, wherein an absorptive, consumable material (42) is positioned in contact with the resin during at least a portion of the curing.
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
B64F 5/00 - Tracé, fabrication, assemblage, nettoyage, entretien ou réparation des aéronefs, non prévus ailleursManipulation, transport, test ou inspection de composants d’aéronefs, non prévus ailleurs
B29C 73/26 - Appareils ou accessoires non prévus ailleurs pour le prétraitement mécanique
B29L 31/30 - Véhicules, p. ex. bateaux ou avions, ou éléments de leur carrosserie
63.
METHOD FOR DESIGNING AND FITTING, VIA INTERFERENCE, AN INSERT INTO AN OPENING IN A NON-METALLIC MATERIAL
Method for inserting an insert (18) into a hole (12) in a composite material (10) includes lowering a temperature of the insert to a reduced temperature at which the material of the insert contracts to a first perimeter, inserting the insert at the reduced temperature into the hole in the composite material, and permitting the temperature of the insert to increase from the reduced temperature to an operational temperature. At the operational temperature, the insert presents a second perimeter greater than the first perimeter so as to be retained within the composite material due to an interference between the insert and the composite material, the interference being such that structural load is transferred from the insert to the composite material and such that dislodging the insert at the operational temperature from the composite material results in damage to the composite material.
B29C 65/56 - Assemblage d'éléments préformésAppareils à cet effet en utilisant des moyens mécaniques
B29C 65/66 - Assemblage d'éléments préformésAppareils à cet effet par libération de contraintes internes, p. ex. par retrait d'un des éléments à assembler
B29C 65/00 - Assemblage d'éléments préformésAppareils à cet effet
F16B 4/00 - Assemblage par retrait, p. ex. en portant les pièces à assembler à des températures différentesMontage à forceAttaches à serrage par friction non largables
64.
APPARATUS AND METHODS FOR DISTRIBUTING ELECTRIC POWER ON AN AIRCRAFT DURING A LIMITED POWER AVAILABILITY CONDITION
Methods and apparatus for distributing electric power from a power source of an aircraft to a plurality of electrical loads of the aircraft during a limited power availability condition are disclosed. An exemplary method comprises: distributing electric power from the power source of the aircraft to the plurality of electrical loads; receiving one or more signals indicative of a demand for electric power by one or more of the plurality of electrical loads; and adjusting the power distribution to the plurality of electrical loads based on the demand for electric power by the one or more plurality of electrical loads. The power distribution is also adjusted to maintain an overall power consumption of the plurality of electrical loads at or below a threshold.
A support assembly (10) having a structural element (12) having first and second non-parallel adjoining surfaces (18), a bracket (14) attached to the structural element (12), and a component support (16). The bracket (14) has a first flange (20) including a first attachment surface (24) adhesively bonded to the first surface (18) of the structural element (12), a second flange (20) including a second attachment surface (24) adhesively bonded to the second surface (18) of the structural element (12), and a connection portion (48) interconnecting the first and second flanges (20), the connection portion (48) extending spaced from the structural element (12) such that a gap (52) is defined therebetween. The component support (16) is engaged to the first flange (20). The connection portion (48) may have a lower resistance to rupture than that of the first and second flanges (20). A method of removably securing a component to a structural element is also discussed.
F16B 11/00 - Assemblage d'éléments structuraux ou parties de machines par collage ou en les pressant l'un contre l'autre, p. ex. soudage sous pression à froid
H02G 3/00 - Installations de câbles ou de lignes électriques ou de leurs tubes de protection dans ou sur des immeubles, des structures équivalentes ou des véhicules
66.
REPAIR INCLUDING A CHAMFERED BRACKET AND A CHAMFERED BRACKET COMPONENT FOR REINFORCING A DAMAGED STRUCTURAL ELEMENT MADE FROM COMPOSITE MATERIALS
A repair for a structural element made from a composite material includes a bracket defining a first surface and a second surface. The first surface is adapted for facing the structural element. A chamfer is located on a first end of the bracket. An angle is defined between a plane of the chamfer and a plane of the first surface, the first surface of the bracket being adapted to be disposed adjacent to a side of the structural element. The repair also includes a sealant material between the bracket and the structural element, where the sealant material occupies a space established between the chamfer and the structural element.
B29C 65/48 - Assemblage d'éléments préformésAppareils à cet effet en utilisant des adhésifs
B29C 73/04 - Réparation d'articles faits de matières plastiques ou de substances à l'état plastique, p. ex. d'objets façonnés ou fabriqués par utilisation de techniques couvertes par la présente sous-classe ou la sous-classe utilisant des éléments préformés
B29C 73/14 - 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 éléments en deux parties qui sont réunies après avoir été posées chacune sur un côté de l'objet
B29C 65/00 - Assemblage d'éléments préformésAppareils à cet effet
An aircraft comprises an aircraft structure, a flight control surface attached to the aircraft structure, and a local hydraulic power pack disposed proximal to the flight control surface. The local hydraulic power pack is configured to provide pressurized hydraulic fluid for actuating the flight control surface. The local hydraulic power pack comprises a reservoir for the hydraulic fluid and two hydraulic pumps for pressurizing the hydraulic fluid.
B64C 13/50 - Dispositifs de transmission avec amplification de puissance utilisant l'énergie électrique
B64C 13/42 - Dispositifs de transmission avec amplification de puissance utilisant la pression d'un fluide comportant des dispositifs de doublement de la commande ou de mise en position de secours
A partition assembly (16) for an aircraft cabin, including a bulkhead (18) with first (28) and second (30) internal compartments having respective first (32) and second (34) open ends defined in a same side of the bulkhead (18), one of the compartments being located aft of the other, a sliding door (36) slidingly supported within the first compartment (28) and slidable out of the first compartment (28) through the first open end (32), and a curtain (42) slidingly engaged to a curtain rail (40), the curtain receivable in the second compartment (30) and slidable along the curtain rail (40) out of the second compartment (30) through the second open end (34). An aircraft curtain rail is also described where the curtain rail and curtain track each have a non-rectilinear profile when viewed in a first plane and when viewed in a second plane perpendicular to the first plane. A method of manufacturing a curtain rail is also discussed.
There is described herein a harness (106) that remains neutral until configured by a configuration device (110). Wires that connect to specific pins responsible for the configuration of a system are taken out and connected to a configuration port (108) on the harness (106). The configuration port (108), when mated with the configuration device (110), sets a configuration setting of the system. The configuration device (110) may be used to set the power and/or signal parameters of the harness (106) for a system or to configure various options within the system itself or another system.
B60R 16/02 - Circuits électriques ou circuits de fluides spécialement adaptés aux véhicules et non prévus ailleursAgencement des éléments des circuits électriques ou des circuits de fluides spécialement adapté aux véhicules et non prévu ailleurs électriques
H01B 7/00 - Conducteurs ou câbles isolés caractérisés par la forme
H02G 3/00 - Installations de câbles ou de lignes électriques ou de leurs tubes de protection dans ou sur des immeubles, des structures équivalentes ou des véhicules
H01R 27/00 - Pièces de couplage adaptées à la coopération avec plusieurs pièces complémentaires dissemblables
H01R 29/00 - Pièces de couplage pour coopération sélective avec une pièce complémentaire de différentes façons pour établir différents circuits, p. ex. pour la sélection de tension, pour la sélection série-parallèle
70.
INDICATING SYSTEMS, DEVICES AND METHODS FOR HIGH-LIFT FLIGHT CONTROL SURFACES OF AIRCRAFT
Systems, devices and methods a for use with one or more high-lift flight control surfaces (24) of aircraft are disclosed. One exemplary method comprises receiving data representative of a commanded configuration (48) for a high-lift flight control surface (24); and on a display device (14) of the aircraft, showing an indicator (30) indicating the commanded configuration and a corresponding commanded position (50) for the high-lift flight control surface (24). The indicator (30) graphically indicates a correlation between the commanded configuration (48) and the corresponding commanded position (50) for the high-lift flight control surface (24).
An aircraft (10) is described as including a reference axis extending along at least a portion of the aircraft, and a propulsion system having a thrust vector feature (43) defining generally a direction of thrust of the turbofan engine (18), the thrust vector feature (43) extending relative to a thrust vector axis, where the turbofan engine (18) is disposed on the aircraft with the thrust vector feature (43) oriented with respect to the reference axis of the aircraft.
B64F 5/00 - Tracé, fabrication, assemblage, nettoyage, entretien ou réparation des aéronefs, non prévus ailleursManipulation, transport, test ou inspection de composants d’aéronefs, non prévus ailleurs
F02K 1/00 - Ensembles fonctionnels caractérisés par la forme ou la disposition de la tubulure de jet ou de la tuyèreTubulures de jet ou tuyères particulières à cet effet
B64C 15/02 - Commande de l'assiette, de la direction du vol ou de l'altitude par jets réactifs les jets étant des jets propulsifs
Cabin air is managed in the aircraft as a function of the minimum requirements for defined air quality needs, temperature control needs, and cabin pressurization needs. Airflow may be varied dynamically as a function of aircraft or cabin altitude, and the minimum requirements for airflow may be determined in real time so as to dynamically set an airflow schedule.
B64D 13/00 - Aménagements ou adaptations des appareils de conditionnement d'air pour équipages d'aéronefs, passagers ou pour emplacements réservés au fret
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
Air quality sensors are incorporated into an aircraft ventilation system in order to detect the nature and concentration of possible contaminants in the air flow passages. Data from the sensors may also be used to monitor air quality trends, determine corrective measures, and provide maintenance alerts. The sensors are provided at strategic locations throughout the ventilation system, such as before and/or after an air compressor and before and/or after a recirculation system, in order to identify where the problem is occurring.
B64D 13/00 - Aménagements ou adaptations des appareils de conditionnement d'air pour équipages d'aéronefs, passagers ou pour emplacements réservés au fret
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
74.
APPARATUS AND METHODS FOR ASSISTING WITH AIRCRAFT MAINTENANCE USING PREDETERMINED MAINTENANCE PROGRAMS
Apparatus and methods for assisting with maintenance and design of one or more structural elements of an aircraft are disclosed. One exemplary method comprises receiving actual utilization data for the aircraft and evaluating the actual utilization data with respect to at least one of a plurality of utilization criteria respectively associated with a plurality of utilization categories for the aircraft where the utilization categories are associated with respective predetermined maintenance programs for the structural element or for the aircraft as a whole. Based on the evaluation of the actual utilization data with respect to the at least one utilization criterion, one of the utilization categories is assigned to the aircraft. Based on the utilization category assigned to the aircraft, one of the predetermined maintenance programs is assigned to the structural element or to the aircraft as a whole.
Systems, devices and methods a for assisting a pilot with aircraft landing are disclosed. One exemplary method comprises receiving data representative of a current approach/landing capability of the aircraft and data representative of an approach/landing intent of the pilot; and showing a combined indicator graphically and simultaneously indicating the current approach/landing capability of the aircraft and the approach/landing intent of the pilot on a display device of the aircraft. The approach/landing intent of the pilot may be graphically indicated via cooperation between a first graphical object of the indicator and a second graphical object of the indicator. The method may graphically indicate a system degradation affecting the current approach/landing capability of the aircraft with the same indicator.
G08G 5/02 - Aides pour l'atterrissage automatique, c. à d. systèmes dans lesquels les données des vols d'avions arrivant sont traitées de façon à fournir les données d'atterrissage
G05D 1/00 - Commande de la position, du cap, de l'altitude ou de l'attitude des véhicules terrestres, aquatiques, aériens ou spatiaux, p. ex. utilisant des pilotes automatiques
G01C 23/00 - Instruments combinés indiquant plus d’une valeur de navigation, p. ex. pour l’aviationDispositifs de mesure combinés pour mesurer plusieurs variables du mouvement, p. ex. la distance, la vitesse ou l’accélération
An acoustic abatement apparatus for an aircraft includes a layer of material disposed exterior to a fuselage of the aircraft, where the layer of material connects to the fuselage to establish a gap between the layer of material and the fuselage, a flexible container disposed in the gap, and at least one acoustic resonator connected to the flexible container. The at least one acoustic resonator is tuned to a predetermined resonator frequency.
B64C 1/40 - Insonorisation ou isolation calorifique
B64C 11/00 - Hélices, p. ex. du type carénéCaractéristiques communes aux hélices et aux rotors pour giravions
G10K 11/172 - Procédés ou dispositifs de protection contre le bruit ou les autres ondes acoustiques ou pour amortir ceux-ci, en général utilisant des effets de résonance
A dual load path assembly (12) comprises an outer pin (14), which has an axial through bore and at least one end that includes a threaded section (30). The threaded section (30) includes at least one slot (32) orientated from the end and extending axially along at least part of the threaded section (30). The assembly (12) also includes an inner pin (16), which is receivable in the through bore of the outer fastener (14). A female fastener (18) comprising at least one notch (38) is receivable on the threaded end of the outer pin (14). A locking plate (20) comprises a through hole via which it is receivable on the shank (17) of the inner pin (16) and at least one projection (34). The locking plate (20) is arranged such that the projection (34) is receivable in both the notch (38) and the slot (32). A locking member (22) engages with the end of the inner pin (16) and abuts a face of the locking plate (20) thereby sandwiching the locking plate (20) between the locking member (22) and the female fastener (18).
F16B 35/04 - Boulons filetésBoulons d'ancrageGoujons filetésVisVis de pression avec tête ou axe de forme particulière permettant de fixer le boulon sur ou dans un objet
F16B 39/04 - Blocage des vis, boulons ou écrous dans lequel le verrouillage s'effectue après vissage avec un organe traversant le filetage d'une pièce au moins, p. ex. une broche, une clavette, une goupille fendue, une vis
78.
SEALING ASSEMBLY AND PLUG FOR NON-DESTRUCTIVE INSPECTION
A plug for inserting into an end of a tubular component to be inspected, including an air discharge unit receivable within the tubular component and having an end surface with a plurality of air outlets defined therein, a flow-directing body receivable within the component extending from the end surface of the air discharge unit with the plurality of outlets located radially outwardly of the flow-directing body, and a sealing member connected to the air discharge unit and having an extended configuration where the sealing member extends outwardly of the perimeter of the air discharge unit. A sealing assembly for a plate component to be inspected and a method of inspecting an outer surface of a component are also discussed. The plug and sealing assembly act to prevent an inspection coupling fluid from flowing on non-inspected surfaces of the component.
G01N 29/28 - Recherche ou analyse des matériaux par l'emploi d'ondes ultrasonores, sonores ou infrasonoresVisualisation de l'intérieur d'objets par transmission d'ondes ultrasonores ou sonores à travers l'objet Détails pour établir le couplage acoustique
79.
COMBINED AIRCRAFT MAINTENANCE ROUTING AND MAINTENANCE TASK SCHEDULING
A method and system for coordinating aircraft maintenance routing and scheduling for a fleet of aircraft over a given time period is described. The method comprises receiving an initial list of due maintenance tasks based on aircraft information of the fleet and a proposed fleet utilization distribution; generating a set of aircraft routes for the fleet, the routes comprising maintenance opportunities for the due maintenance tasks, the due maintenance tasks being considered as aggregated maintenance constraints for generation of the aircraft routes; scheduling the due maintenance tasks into the maintenance opportunities while respecting target due dates; and in case of infeasibility for maintenance task scheduling within the maintenance opportunities of the aircraft routes, regenerating the set of aircraft routes for the fleet using the aggregated maintenance constraints and additional constraints, and rescheduling the due maintenance tasks using the regenerated set of aircraft routes.
G06Q 10/06 - Ressources, gestion de tâches, des ressources humaines ou de projetsPlanification d’entreprise ou d’organisationModélisation d’entreprise ou d’organisation
Methods and systems useful during assembly of aircraft are disclosed. One such method comprises loading a fuselage of the aircraft that is unassembled with a wing of the aircraft to obtain a configuration of the fuselage corresponding to when the fuselage is assembled with the wing. The method also comprises calibrating a device of a navigation system of the aircraft when the fuselage is unassembled with the wing and is being loaded to obtain the loaded configuration and, after calibrating the device of the navigation system, assembling the fuselage with the wing.
B64F 5/00 - Tracé, fabrication, assemblage, nettoyage, entretien ou réparation des aéronefs, non prévus ailleursManipulation, transport, test ou inspection de composants d’aéronefs, non prévus ailleurs
Methods and related apparatus for improving synchronization of two or more engines on an aircraft are disclosed. Such method may be used where each engine comprises a first spool and a second spool, and, where a rotational speed of a first spool of a first engine has been substantially synchronized with a rotational speed of a first spool of a second engine. An exemplary method comprises receiving a value of a sensed parameter useful in controlling the first engine; adding a bias to the value; and using the biased value for controlling the first engine to cause a change in rotational speed of the second spool of the first engine in relation to the rotational speed of the first spool of the first engine.
B64D 31/12 - Dispositifs amorçant la mise en œuvre actionnés automatiquement pour équilibrer ou synchroniser les groupes moteurs
F02C 9/18 - Commande du débit du fluide de travail par prélèvement, par bipasse ou par action sur des raccordements variables du fluide de travail entre des turbines ou des compresseurs ou entre leurs étages
F02C 9/28 - Systèmes de régulation sensibles aux paramètres ambiants ou à ceux de l'ensemble fonctionnel, p. ex. à la température, à la pression, à la vitesse du rotor
F02C 9/42 - Commande de l'alimentation en combustible spécialement adaptée à la commande simultanée d'au moins deux ensembles fonctionnels
There are described herein methods and systems for manufacturing and/or assembling components having datum features thereon used to derive datum reference frames. The datum reference frames provided on the components may serve as both manufacturing and assembly datum reference frames.
B64F 5/00 - Tracé, fabrication, assemblage, nettoyage, entretien ou réparation des aéronefs, non prévus ailleursManipulation, transport, test ou inspection de composants d’aéronefs, non prévus ailleurs
G05B 19/418 - Commande totale d'usine, c.-à-d. commande centralisée de plusieurs machines, p. ex. commande numérique directe ou distribuée [DNC], systèmes d'ateliers flexibles [FMS], systèmes de fabrication intégrés [IMS], productique [CIM]
B23P 19/10 - Alignement de pièces qui doivent être assemblées entre elles
83.
APPARATUS FOR OBSTRUCTING AIR FLOW THROUGH AN APERTURE FOR A DUCT IN AN AIRCRAFT WING
Apparatus for obstructing air flow through an aperture in an aircraft wing where a movable anti-icing duct extends through the aperture are disclosed. An exemplary apparatus comprises a base member (40) configured to be secured to the duct and a first seal member (42) configured to obstruct air flow through the aperture. The first seal member comprises a proximal portion (42A) connected to the base member and a distal portion (42B) configured to movably contact an inner surface of a skin of the wing. The use of such apparatus may reduce the amount of leakage flow from the high pressure lower wing surface to the low pressure upper wing surface through the aperture and thereby reduce the loss of lift associated with such leakage flow.
A sealed component assembly within an aircraft, comprising first 10 and second 12 components each facing surfaces, and a sealing member 20 extending between the facing surfaces. The sealing member includes a conductive portion 22 sandwiched between first 24 and second 26 sealing portions. The sealing portions extend between and in contact with the facing surfaces, and are made of a sealing material. The conductive portion is in contact with conductive regions of the facing surfaces and defines an electrical connection therebetween. The conductive portion is more conductive than the sealing portions. In a particular embodiment, the components are a floor panel and a floor beam. A sealing member 20 for a connection between two aircraft components is also discussed.
F16J 15/06 - Joints d'étanchéité entre surfaces immobiles entre elles avec garniture solide comprimée entre les surfaces à joindre
F16J 15/12 - Joints d'étanchéité entre surfaces immobiles entre elles avec garniture solide comprimée entre les surfaces à joindre par garniture non métallique par renforcement ou couverture métallique
There is described a method for referencing a composite structure within an online vision inspection system. Referencing is performed independently from a positioning accuracy of an automated tool with which the composite structure is manufactured. Reference targets provided on a contour of a lay-up surface are used to correlate an image reference system with a mold reference system.
G01B 11/25 - Dispositions pour la mesure caractérisées par l'utilisation de techniques optiques pour mesurer des contours ou des courbes en projetant un motif, p. ex. des franges de moiré, sur l'objet
Sound absorbers and airframe components comprising such sound absorbers are disclosed. In one embodiment, an airframe component comprises an aerodynamic surface (48) and a sound absorber (38). The sound absorber (38) comprises a perforated panel (40) having a front side exposed to an ambient environment outside of the airframe component and an opposite back side. The panel (40) comprises perforations extending through a thickness of the panel for permitting passage of sound waves therethrough. The sound absorber (38) also comprises a boundary surface spaced apart from the perforated panel. The boundary surface and the back side of the perforated panel (40) at least partially define a cavity in the airframe component for attenuating some of the sound waves entering the cavity via the perforations in the perforated panel (40).
B64C 1/40 - Insonorisation ou isolation calorifique
B64C 21/02 - Moyens permettant d'influencer l'écoulement d'air sur les surfaces des aéronefs en agissant sur la couche limite par utilisation de fentes, de conduits, de surfaces poreuses ou de dispositifs similaires
A headrest for a seat of a vehicle includes a body securable to the seat, a side portion adjacent the body, a receiver pivotally attached to the body, a slide attached to the side portion so as to be movable along the receiver between a first position in which the side portion is in a retracted position and a second position in which the side portion is in an extended position, and a friction member on one of the receiver and the slide. A securing mechanism causes the friction member to hold the slide in a selected position relative to the receiver.
Components having fibre-reinforced composite structures are disclosed. The component comprises a plurality of structural fibres embedded in a cured matrix material and a plurality of nanostructures such as carbon nanotubes extending from one or more of the structural fibres. In some embodiments a density of the nanostructures is at least 107 nanostructures per cm2 of surface area of the one or more structural fibres. In some embodiments, the nanostructures extend from an outer fibre proximal to an outer surface of the component but not from an inner fibre distal from the outer surface. In some embodiments the one or more structural fibres from which the nanostructures extend are free of a sizing agent.
B32B 5/26 - Produits stratifiés caractérisés par l'hétérogénéité ou la structure physique d'une des couches caractérisés par la présence de plusieurs couches qui comportent des fibres, filaments, grains ou poudre, ou qui sont sous forme de mousse ou essentiellement poreuses une des couches étant fibreuse ou filamenteuse un autre couche également étant fibreuse ou filamenteuse
B32B 5/02 - Produits stratifiés caractérisés par l'hétérogénéité ou la structure physique d'une des couches caractérisés par les caractéristiques de structure d'une couche comprenant des fibres ou des filaments
C08J 5/24 - Imprégnation de matériaux avec des prépolymères pouvant être polymérisés en place, p. ex. fabrication des "prepregs"
B29C 70/08 - Façonnage de matières composites, c.-à-d. de matières plastiques comprenant des renforcements, des matières de remplissage ou des parties préformées, p. ex. des inserts comprenant uniquement des renforcements, p. ex. matières plastiques auto-renforçantes des renforcements fibreux uniquement comprenant des combinaisons de différentes formes de renforcements fibreux incorporés dans une matrice, formant une ou plusieurs couches, avec ou sans couches non renforcées
A composite component (16) for a vehicle (10) includes a laminate (18) made from a composite material, a first pad-up area (22) applied to the laminate (18), where the first pad-up area (22) includes a plurality of first tows laid next to one another in a side-by-side arrangement and where the first pad-up area (22) defines a first fiber orientation, and a second pad-up area (24), where the second pad-up area (24) includes a plurality of second tows laid next to one another in a side-by-side arrangement and where the second pad-up area (24) defines a second fiber orientation that differs by a predetermined angle from the first fiber orientation. The first pad-up area (22) and the second pad-up area (22) intersect at an intersecting area and together form a first pad-up ply on the laminate (18).
B29C 70/34 - Façonnage par empilage, c.-à-d. application de fibres, de bandes ou de feuilles larges sur un moule, un gabarit ou un noyauFaçonnage par pistolage, c.-à-d. pulvérisation de fibres sur un moule, un gabarit ou un noyau et façonnage ou imprégnation par compression
B29C 70/38 - Empilage automatisé, p. ex. utilisant des robots, par application de filaments selon des modèles prédéterminés
B29D 99/00 - Matière non prévue dans les autres groupes de la présente sous-classe
There is described an online inspection method and system having an illumination system that provides bright-field and dark-field illumination concurrently or sequentially, at varying intensities, in order to acquire images that may be read by an image processing device. The image processing device may obtain measurements of features in the images and evaluate acceptability of the features.
There is described herein a method and system for the configuration of vehicle management components using in-vehicle position detection. The in- vehicle position detection may also be used for providing a floor plan of the vehicle. In some embodiments, in-vehicle position detection may be used concurrently for configuring vehicle management components and for providing floor plans.
Precursors and methods for manufacturing perforated composite parts are disclosed. An exemplary precursor (19) comprises structural fibres (24,28) embedded in a cured matrix material (24,26) and interposed between two removable plies (20). The precursor may also comprise a sacrificial fibre (28) extending through the removable plies (20), the matrix material (24,26) and between the structural fibres (24,28). An exemplary method comprises removing the removable plies (20) from the precursor (19) and removing the sacrificial fibre (28) from the precursor after removing the removable plies to form a through hole in the precursor (19) at a location of the sacrificial fibre (28).
B29C 70/54 - Parties constitutives, détails ou accessoiresOpérations auxiliaires
B32B 5/06 - Produits stratifiés caractérisés par l'hétérogénéité ou la structure physique d'une des couches caractérisés par les caractéristiques de structure d'une couche comprenant des fibres ou des filaments caractérisés par une couche fibreuse imbriquée ou cousue avec une autre couche, p. ex. de fibres, de papier
B32B 7/08 - Liaison entre couches par des moyens mécaniques
93.
AIRCRAFT CABINET WITH DETACHABLE OUTER PANELS AND ATTACHMENT MECHANISM THEREFOR
A cabinet for installation in an aircraft, having a shell (22) defining a load-bearing structure of the cabinet and an outer panel (18) configured to be detachably connected to the shell (22), the outer panel (18) defining at least a part of the visible surfaces of the cabinet. The outer panel (18) is detachably connected to the shell (22) in a stationary position relative to the shell (22) through engagement of complementary attachment members (50, 51) respectively attached to the outer panel (18) and to the shell (22), the complementary attachment members (50, 51) allowing an adjustment of the stationary position of the outer panel (18) relative to the shell (22) when the outer panel (18) is detached from the shell (22). A method of manufacturing a cabinet for an aircraft is also discussed.
Apparatus and device for manufacturing and repairing fibre-reinforced composite materials are disclosed. In various embodiments, the apparatus and device disclosed herein use a resin retaining/releasing device comprising resin having a viscosity that is temperature dependent for infusion into a region of a part. The resin retaining/releasing device comprises a first sheet (18) and an opposite second sheet (20) at least partially enclosing the quantity of resin. The first sheet (18) and the second sheet (20) are gas-permeable. The second sheet (20) is substantially resin-impermeable when the viscosity of the resin is above a threshold viscosity and resin-permeable when the viscosity of the resin is below the threshold viscosity.
B29C 73/02 - Réparation d'articles faits de matières plastiques ou de substances à l'état plastique, p. ex. d'objets façonnés ou fabriqués par utilisation de techniques couvertes par la présente sous-classe ou la sous-classe utilisant un liquide ou un matériau pâteux
B29C 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
There is described herein an inspection tool for use during the inspection of components as manufactured. The inspection tool allows the comparison of measurement data with nominal data and provides complementary information with regards to at least one feature of the component.
G01B 21/04 - Dispositions pour la mesure ou leurs détails, où la technique de mesure n'est pas couverte par les autres groupes de la présente sous-classe, est non spécifiée ou est non significative pour mesurer la longueur, la largeur ou l'épaisseur en mesurant les coordonnées de points
There is described herein a method and system for inspecting various fabrication features of composite components, such as tow/ply location, angle deviation, and gap size, using a laser-vision assembly. In some embodiments, a tolerance for that fabrication feature is provided as an inspection feature and a laser projecting device projects the inspection feature onto the material. Alternatively or in combination thereof, a calibration feature is projected onto the material, the calibration feature comprising known dimensional information. An image acquisition device acquires an image of the material with the inspection/calibration feature(s) projected thereon. The images can be analysed automatically or manually to detect whether the fabrication features are compliant and/or to obtain measurement data of the fabrication features.
G01B 21/04 - Dispositions pour la mesure ou leurs détails, où la technique de mesure n'est pas couverte par les autres groupes de la présente sous-classe, est non spécifiée ou est non significative pour mesurer la longueur, la largeur ou l'épaisseur en mesurant les coordonnées de points
G01B 11/00 - Dispositions pour la mesure caractérisées par l'utilisation de techniques optiques
G01B 11/25 - Dispositions pour la mesure caractérisées par l'utilisation de techniques optiques pour mesurer des contours ou des courbes en projetant un motif, p. ex. des franges de moiré, sur l'objet
A skin for an aircraft is configured to be disposed on a first rigid member (182). The first rigid member has at least a portion of a structural frame for the aircraft. The skin is configured to be disposed on a second rigid member (184) that has at least a portion of the structural frame for the aircraft. The second rigid member (184) is moveable with respect to the first rigid member (182) and a distance is defined between the first rigid member and the second rigid member. A morphing member of the skin extends between the first rigid member and the second rigid member. The morphing member compensates for at least one of a change in the distance and a change in an orientation between the first rigid member and the second rigid member.
There is described a method and system for determining a sampling plan using a statistical analysis of different regions of at least one component and determining a level of performance for each of the regions. Subsequent components are then inspected using the sampling plan. Results from the inspection may be used to update and/or modify the sampling plan in a feedback loop.
A method, system and controller for controlling power supplied to a heating device of a window on a vehicle, comprising receiving information indicative of at least one parameter associated with operation of the vehicle, generating a power signal at least in part on a basis of the information indicative of the at least one parameter and stored control logic, the power signal being indicative of a power modulation level for power to be supplied to the heating device and transmitting the power signal to a power regulator for causing power to be supplied to the heating device in accordance with the power modulation level.
An air gasper (air) for a vehicle includes an air inlet (26), a first housing (24) disposable through a panel in the vehicle (12), the first housing (24) being connected to the air inlet (26), a second housing (70) disposed within the first housing (24), an air outlet (72) disposed within the second housing (70), downstream of the air inlet (26), and a first mechanism (102, 70) connected between the first housing (24) and the second housing (70). The first mechanism (102, 70) permits the second housing (70) to be stowed within the first housing (24) in a stowed position and also permits the second housing (70) to extend outwardly from the first housing (24) in a deployed position.
B64D 13/00 - Aménagements ou adaptations des appareils de conditionnement d'air pour équipages d'aéronefs, passagers ou pour emplacements réservés au fret
