A method of making an aircraft acoustic structural panel (10) begins with preforming a core honeycomb laminate (12) having preformed foam (3) bonded inside cells (14) thereof by a distinct adhesive (2). The preformed honeycomb laminate (12) is then stacked between opposite top and bottom structural outer laminates (16,18). The stacked honeycomb laminate (12) and outer structural laminates (16,18) are then compressed together under heat and pressure into a unitary structural panel (10) having the core honeycomb laminate (12) integrally bonded between outer skins (20,22). The outer laminates (16,18) may include imperforate acoustic septums (4) bounding the core honeycomb laminate (12) followed by an outer honeycomb (5) and structural fiber layers (6,7,8) defining the outer skins (20,22).
F02C 7/045 - Entrées d'air pour ensembles fonctionnels de turbines à gaz ou de propulsion par réaction comportant des dispositifs destinés à supprimer le bruit
A radome assembly (20) includes a frame (30) conforming in contour with an aircraft fuselage (14) for being fixedly mounted thereto. A radome (32) having an aerodynamically streamlined elongate contour including a central bulb (34) is spaced from the frame (30) to house an antenna (26) therein, the radome (32) being tuned in configuration to define an unobstructed radio -frequency (RF) window (28) diverging outwardly from atop the frame (30). The radome (32) is pivotally mounted atop the frame (30) by a hinge (36,74,78) hidden inside the frame (30) below the RF window (28) when the radome (32) is stowed closed atop the frame (30) and antenna (26).
B64C 1/36 - FuselagesCaractéristiques structurales communes aux fuselages, voilures, surfaces stabilisatrices ou organes apparentés adaptés pour recevoir des antennes ou des radômes
A method of machining a cellular core (14) includes mounting the core (14) atop a table (12) in a multi-axis Computerized Numerical Controlled (CNC) machine (10). The machine (10) is operated to self-scan the core (14) and self- recognize individual cells (30) arranged laterally in columns and longitudinally in rows. A machining path (E) is self-generated from the pre-recognized cells (30), and the core (14) is then machined along the self-generated machining path (E).
B23K 26/38 - Enlèvement de matière par perçage ou découpage
B23K 26/40 - Enlèvement de matière en tenant compte des propriétés du matériau à enlever
B26D 5/34 - Dispositions pour manœuvrer et commander les machines ou les dispositifs de coupe, découpage, poinçonnage, perforation ou séparation autrement que par coupe l'organe de coupe et d'avance de la pièce ayant une action conjuguée l'organe de coupe étant commandé par balayage d'un support d'enregistrement le balayage étant effectué par un dispositif photo-sensible
G05B 19/18 - Commande numérique [CN], c.-à-d. machines fonctionnant automatiquement, en particulier machines-outils, p. ex. dans un milieu de fabrication industriel, afin d'effectuer un positionnement, un mouvement ou des actions coordonnées au moyen de données d'un programme sous forme numérique
G05B 19/402 - Commande numérique [CN], c.-à-d. machines fonctionnant automatiquement, en particulier machines-outils, p. ex. dans un milieu de fabrication industriel, afin d'effectuer un positionnement, un mouvement ou des actions coordonnées au moyen de données d'un programme sous forme numérique caractérisée par des dispositions de commande pour le positionnement, p. ex. centrage d'un outil par rapport à un trou dans la pièce à usiner, moyens de détection additionnels pour corriger la position
G05B 19/4093 - Commande numérique [CN], c.-à-d. machines fonctionnant automatiquement, en particulier machines-outils, p. ex. dans un milieu de fabrication industriel, afin d'effectuer un positionnement, un mouvement ou des actions coordonnées au moyen de données d'un programme sous forme numérique caractérisée par la programmation de pièce, p. ex. introduction d'une information géométrique dérivée d'un dessin technique, combinaison de cette information avec l'information d'usinage et de matériau pour obtenir une information de commande, appelée programme de pièce, pour la machine à commande numérique [CN]
4.
ASYNCHRONOUS TENDERING FOR VARIABLE CHARACTERISTIC ASSETS
Utilities that allow for the asynchronous tendering for variable characteristic assets. In one aspect, a utility for returning a strike price based on the iterative comparison of a received first listing object with a received first offer object, both corresponding to a first variable characteristic asset. At least one of the first listing object and the first offer object may include a time-dependent price such that the iterative comparison may facilitate the determination of a time-dependent price range corresponding to the variable characteristic asset at a given time. In this regard, the strike price may be returned at least partially based on the time-dependent price range. Additionally, the present disclosure includes embodiments related to the verification of a condition-dependent status of the first variable characteristic asset and a generation of comparison metrics associated with the asynchronous tendering.
G06Q 30/06 - Transactions d’achat, de vente ou de crédit-bail
G06Q 10/04 - Prévision ou optimisation spécialement adaptées à des fins administratives ou de gestion, p. ex. programmation linéaire ou "problème d’optimisation des stocks"
A bonding method includes vacuum bagging a second metal plate (12) atop a first metal plate (10), with a thermosetting adhesive (16) in a lap joint (22) therebetween covered in turn by a porous peel ply (28) and a porous breather ply (30); the plates (10, 12) being initially clamped together by applying vacuum through the breather ply (30); and thermally curing the adhesive (16), with the breather and peel plies (30,28) being preselected to capture adhesive seepage (38) from the lap joint (22) and removed with the plies (28,30) to correspondingly reduce cured adhesive flash (40).
B23K 37/08 - Dispositifs ou procédés auxiliaires non spécialement adaptés à un procédé couvert par un seul des autres groupes principaux de la présente sous-classe pour l'ébavurage
B32B 15/04 - Produits stratifiés composés essentiellement de métal comprenant un métal comme seul composant ou comme composant principal d'une couche adjacente à une autre couche d'une substance spécifique
B32B 15/092 - Produits stratifiés composés essentiellement de métal comprenant un métal comme seul composant ou comme composant principal d'une couche adjacente à une autre couche d'une substance spécifique de résine synthétique comprenant des résines époxy
A hybrid frame (18) is fabricated by initially forming a stack of fibrous layers (8) in an annular pattern. An annular metal trim (54) is separately formed to conform with the annular pattern. The trim (54) is trapped in a lower mold (70) having a complementary lower mold channel (74). The stacked layers (8) are trapped atop the trim (54) in the lower mold channel (74). An upper mold (72) is pressed atop the stacked layers (8) for compression co-molding together in the lower mold (74) the stacked layers (8) and trim (54) to co-form the hybrid frame (18).
A thrust reverser nozzle (22) for an engine nacelle (20) includes opposite and asymmetrically pivoting first and second doors (24,26) defining a nacelle aft section (20a), first and second trailing edges (24a, 26a) of the first and second doors (24,26) adjacent to an outlet (28) of the nacelle, the doors being pivotable simultaneously between a stowed position and a deployed position such that the first trailing edge (24a) is positioned behind the second trailing edge (26a) when the doors are in the deployed position, and the first and second fairings (34,36) attached to the first and second doors in relative fixed positions to the first and second doors respectively Male contour middle portions (38) of the first fairings (34) may complementarily match female contour middle portions (40) of the second fairings (36) and are received within the female contour middle portion when the doors are in the stowed position.
A pair of laminated panels (40) are simultaneously manufactured in a single panel press (10). A thermal band (32) is stacked between two panel sets (42) and then the two panel sets (42) are simultaneously heated and compressed together in a common stack (44) with the band (32), with the band (32) being separately heated.
B32B 37/06 - Procédés ou dispositifs pour la stratification, p. ex. par polymérisation ou par liaison à l'aide d'ultrasons caractérisés par le procédé de chauffage
An erosion shield (54) for an aircraft window (12) includes an annular band (56) having a radially outer brim (58) and a radially inner clip (60). The shield (54) is sized to cover a composite window frame (18) having an outer rim (22) and an inner sash (24) around a central aperture (26) in which is mounted a window pane (20). The clip (60) is asymmetrical around the central aperture (26) to protect the sash (24) and permit assembly of the shield (54) thereto.
An aircraft window frame (18) includes a laminated outer rim (22) and inner sash (24) having a central aperture (26) for receiving a window pane (20). The sash (24) is transversely offset from the rim (22) and they include different layers (1-7) between the opposite inboard and outboard sides (28,20) of the frame (18).
A bonding method includes vacuum bagging a second metal plate (12) atop a first metal plate (10), with a thermosetting adhesive (16) in a lap joint (22) therebetween covered in turn by a porous peel ply (28) and a porous breather ply (30); the plates (10, 12) being initially clamped together by applying vacuum through the breather ply (30); and thermally curing the adhesive (16), with the breather and peel plies (30,28) being preselected to capture adhesive seepage (38) from the lap joint (22) and removed with the plies (28,30) to correspondingly reduce cured adhesive flash (40).
B23K 37/08 - Dispositifs ou procédés auxiliaires non spécialement adaptés à un procédé couvert par un seul des autres groupes principaux de la présente sous-classe pour l'ébavurage
B32B 15/04 - Produits stratifiés composés essentiellement de métal comprenant un métal comme seul composant ou comme composant principal d'une couche adjacente à une autre couche d'une substance spécifique
B32B 15/092 - Produits stratifiés composés essentiellement de métal comprenant un métal comme seul composant ou comme composant principal d'une couche adjacente à une autre couche d'une substance spécifique de résine synthétique comprenant des résines époxy
A thrust reverser nozzle (22) for an engine nacelle (20) includes opposite and asymmetrically pivoting first and second doors (24,26) defining a nacelle aft section (20a), first and second trailing edges (24a, 26a) of the first and second doors (24,26) adjacent to an outlet (28) of the nacelle, the doors being pivotable simultaneously between a stowed position and a deployed position such that the first trailing edge (24a) is positioned behind the second trailing edge (26a) when the doors are in the deployed position, and the first and second fairings (34,36) attached to the first and second doors in relative fixed positions to the first and second doors respectively Male contour middle portions (38) of the first fairings (34) may complementarily match female contour middle portions (40) of the second fairings (36) and are received within the female contour middle portion when the doors are in the stowed position.
F02K 1/60 - Inversion du jet principal par blocage de l'échappement vers l'arrière à l'aide d'éléments pivotants ayant la forme de paupières ou de coquilles, p. ex. inverseurs du type se trouvant en aval de la sortie de la tuyère en position de fonctionnement
F02K 1/76 - Commande ou régulation des inverseurs de poussée
An erosion shield (54) for an aircraft window (12) includes an annular band (56) having a radially outer brim (58) and a radially inner clip (60). The shield (54) is sized to cover a composite window frame (18) having an outer rim (22) and an inner sash (24) around a central aperture (26) in which is mounted a window pane (20). The clip (60) is asymmetrical around the central aperture (26) to protect the sash (24) and permit assembly of the shield (54) thereto.
