A hollow manufactured body has at least one wall of non-ferromagnetic material with an outer surface and an inner surface facing a cavity of the body. Two mutually magnetically attracted sliders are positioned on the inner and outer surfaces. The outer slider is moved manually across the outer surface to a predetermined point where the wall thickness is to be detected; the inner slider on the inner surface follows the movements of the outer slider due to the effect of the magnetic attraction. A transducer on the outer slider is used to measure the force required to move a magnet away from the outer surface of the wall. The value of the thickness of the wall at the predetermined point is then derived from the measured force.
G01L 1/00 - Mesure des forces ou des contraintes, en général
G01B 7/06 - Dispositions pour la mesure caractérisées par l'utilisation de techniques électriques ou magnétiques pour mesurer la longueur, la largeur ou l'épaisseur pour mesurer l'épaisseur
2.
System and method of automatic piloting for in-flight refuelling of aircraft, and aircraft comprising said system
An automatic-piloting system configured for being set on a receiver aircraft and for controlling operations of in-flight refuelling of said receiver aircraft, comprising: first detection means, set on the receiver aircraft and configured for acquiring first geometrical information associated to a first detection area and a second detection area belonging to a tanker aircraft, the first and second detection areas being linked together by a geometrical relation known to the automatic-piloting system; processing means, configured for determining, on the basis of the first geometrical information acquired, first position information associated to a relative position of the receiver aircraft with respect to the tanker aircraft; and an automatic-pilot device coupled to the processing means and configured for varying flight parameters of the receiver aircraft on the basis of the first position information.
G06F 7/00 - Procédés ou dispositions pour le traitement de données en agissant sur l'ordre ou le contenu des données maniées
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
3.
Method of manufacturing a curved structural element made of composite material and having a complex, open cross-section
A method of manufacturing a curved structural element made of composite material has a complex, open cross-section the structural element is formed by the assembly of components made of composite material. A plurality of flat, fresh components are prepared, each component being constituted by a flat layer of curved fibres previously infused with resin, combined with a pre-impregnated layer with straight fibres. Hot-forming of the flat, raw components is then performed. The hot-formed, fresh components are then assembled in accordance with a predetermined sequence on a polymerization tool. The tool includes a shaped, inflatable device astride which a C-shaped raw component is deposited. Finally, the fresh components assembled on the tool are subjected to a polymerization cycle in an autoclave. The inflatable device is inflated by the pressure produced in the autoclave to apply a predetermined pressure from the inside of the C-shaped fresh component.
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
A braking system for an aircraft provided with undercarriage, wherein an axial-flux reversible electrical machine is associated to at least one wheel of the undercarriage and is set in rotation by the rotation of the wheel. Current-dissipator is provided, which can be connected to the windings of the axial-flux reversible electrical machine during rotation of the wheel in the landing phase for dissipating in the current-dissipator the induced currents generated by the machine, which behaves as current generator, and producing a braking effect that slows down the movement of the wheel. An epicyclic reducer is provided between the wheel of the undercarriage and the rotor of the reversible electrical machine. The epicyclic reducer provides a transmission ratio T in such a way that the rotor will turn at a velocity Tω with respect to the velocity of rotation ω of the wheel.
In order to repair a composite-material panel forming part of the external surface of an aircraft, a portable device is applied onto that surface, the portable device including an inflatable chamber consisting of a flexible and airtight membrane and a concave body of rubber-like material sealed with the membrane. The concave body incorporates an inextensible inner reinforcement. Pressurized air is introduced into the chamber via a valve. A further valve, which passes through the membrane in a zone of the membrane external to the chamber, is used to suck air from one side of the membrane to the other.
A beam of fiber-reinforced curable thermosetting composite material is preliminarily assembled in an uncured condition. The beam is placed between two forming tools, namely a lower and an upper tool, shaped in such a way as to give the lower and upper flanges a predetermined shape, at least one of the flanges having a non-rectilinear profile viewed in a longitudinal vertical plane. Two longitudinally elongate rigid inserts are placed between the flanges at the sides of the web and are covered in respective airtight tubular bags. The spaces between the upper tool and the lower tool on the two opposite longitudinal sides are sealed. The open opposite ends of the tubular bags are also sealed in such a manner that the pressure applied in an autoclave during the step of curing causes the tubular bags to swell and presses them against the two opposite faces of the web and against the flanges of the beam. On completion of curing, the upper forming tool is removed and the inserts are extracted sideways.
B32B 37/10 - Procédés ou dispositifs pour la stratification, p. ex. par polymérisation ou par liaison à l'aide d'ultrasons caractérisés par la technique de pressage, p. ex. faisant usage de l'action directe du vide ou d'un fluide sous pression
7.
Process for preparing self-healing composite materials of high efficiency for structural applications
A process is for preparing a self-healing composite material including a matrix of epoxy polymer in which a catalyst of ring opening metathesis reaction and vessels containing at least one monomer able to polymerize due to a ring opening metathesis reaction are dispersed. The process includes the preliminary step of dispersing at molecular level the catalyst in a mixture containing at least one precursor of the epoxy polymer, and then the steps of dispersing, in the mixture, the vessels and a tertiary amine acting as curing agent of the precursor, and the step of curing the mixture by at least a first heating stage performed at a temperature between 70 and 90° C. for a time between 1 and 5 hours, and a second heating stage performed at a temperature between 90 and 170° C. for a time between 2 and 3 hours.
C08G 59/32 - Composés époxydés contenant au moins trois groupes époxyde
B32B 27/38 - Produits stratifiés composés essentiellement de résine synthétique comprenant des résines époxy
B32B 33/00 - Produits stratifiés caractérisés par des propriétés particulières ou des caractéristiques de surface particulières, p. ex. par des revêtements de surface particuliersProduits stratifiés conçus pour des buts particuliers non couverts par une seule autre classe
8.
Method of manufacturing a fuselage frame of composite material
For an arcuate structural member (10) of a fuselage frame, tapes of resin pre-impregnated unidirectional fibers are used. The member (10) includes a web (11) lying in a radial plane and a radially outer cylindrical flange (12). An elongate, arcuate forming mandrel (M1) having a flat radial surface (F) forming an angular edge (D) with a radially outer, convex cylindrical surface (S) is used and a series of promontories (P) radiating outwardly with respect to the cylindrical surface (S) are provided. Layers of pre-impregnated composite material are laid on the mandrel (M1) to form a first flat arcuate laminate (20′), with a part (20″) of the laminate projecting radially outwardly beyond the angular edge (D). The mandrel (M1), the laminate (20′) and the promontories (P) are covered with a membrane (E). A vacuum is then applied to urge the projecting part (20″) of the laminate against the cylindrical surface (S) and against the promontories (P). Contact of the projecting part (20″) with the cylindrical surface (S) near the promontories is prevented or retarded. Finally, discrete portions of the projecting part (20″) near the promontories are removed, obtaining peripheral cavities (15) spaced apart from one another.
A method for prognostics of a structure subject to loads, particularly an aircraft structure, includes, detecting the state (strains) of the structure at multiple primary points and additional points. The loads acting on the structure associated with the state detected in the primary points are determined. Based on the determined loads, the state of the structure in the additional points is estimated. The estimated state of the structure is compared with the state detected in the additional points. A soundness state of the structure is assessed if the estimated and detected values of the state quantity are in agreement, or a defectiveness state of the structure if such values differ.
An aircraft chaff dispenser includes an elongated hollow housing intended to be fixed to the structure of the aircraft so as to be oriented in the longitudinal direction of the aircraft. The housing has a pair of side walls and the front of each side wall is provided with a pair of lateral air intakes each having a circular through-hole with a diameter d and a fence located behind the hole in the longitudinal direction, or in the direction of travel, of the aircraft at a distance 1 from the center of the hole and having a shape in the form of a horizontally lying V with its vertex directed away from the hole. The diameter d of the hole is between 8 and 12 mm. The ratio h/1 between the height h of the fence at the vertex of the V and the distance 1 is between 0.8 and 1, while the ratio h/d between the height h and the diameter d is between 1.5 and 2.
B64D 1/00 - Largage, éjection ou réception, en cours de vol, d'objets, de liquides ou similaires
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
11.
A METHOD OF MANUFACTURING STIFFENED PANELS MADE FROM COMPOSITE MATERIAL
A stringer (16) of fiber reinforced polymerizable thermosetting composite material is provided, the stringer having a cross section of closed or concave shape with two opposite side flanges (16a) that are brought into contact with a skin panel (14) of fiber reinforced polymerizable or polymerized thermosetting composite material. An elongate support (10) coated with a film bag (11) is positioned in a cavity defined between the stringer and the skin panel. The bottom of this assembly rests on a stiff forming tool (15) while the top is covered by a caul plate (17) having a profile congruent with a part of the assembly to be cured. In an autoclave, pressure is applied to the composite material by the tubular inner bag (11) and through the caul plate (17). The pressure is transmitted without the interposition of intermediate mandrels.
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 70/44 - 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
B29D 99/00 - Matière non prévue dans les autres groupes de la présente sous-classe
12.
Apparatus for the infusion of resin into a preform in a closed mould
A tool for the infusion of a resin into a preform made of fiber material includes a mould which can be closed around the preform and in the body of which at least one inlet duct is formed to allow resin to be injected into the mould so that the resin can be infused into the preform. At least one reservoir which can contain the resin, is also formed in the body of the mould and is connected to the at least one inlet duct. The mould can be inserted in an autoclave and the reservoir is configured to permit the transfer of the resin from the reservoir to the inlet duct under the effect of the temperature and of the pressure that are produced in the autoclave, thus allowing the resin to be injected into the mould.
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
13.
Method for applying a vacuum bag around a fuselage barrel made of composite material to be polymerized
A vacuum bag is applied around a fuselage barrel made of composite material to be polymerized, formed by lamination on the outer surface of a mandrel having the form of a solid of rotation about a longitudinal axis. A bag material in the form of a sheet having a transverse width corresponding to the longitudinal length of the fuselage barrel is provided alongside the mandrel. A first transverse end portion of the sheet is fastened or sealed on the outer surface of the barrel or the mandrel. Then the mandrel is rotated around the axis, so as to wrap the sheet about the barrel. While the mandrel rotates, the opposite axial end edges of the sheet are sealed on the mandrel. Finally, a second transverse end portion of the sheet is sealed on the outer surface of the barrel or the mandrel.
A starting and electricity generating system for a reciprocating engine in which at least one piston (2) is movable in opposite directions in a respective combustion chamber (4) to rotate a driving shaft (9) coupled to a flywheel adapted to dynamically absorb a part of the driving torque generated during the active working phases of the piston in order to return it during the phases in which the piston absorbs work. The flywheel consists of a rotor (20) of an electric, reversible axial flow machine (21) which has a stator (24) carried by the engine (1).
F02N 11/04 - Démarrage des moteurs au moyen de moteurs électriques les moteurs étant associés avec des générateurs de courant
H02K 21/24 - Moteurs synchrones à aimants permanentsGénératrices synchrones à aimants permanents avec des induits fixes et des aimants tournants avec des aimants disposés axialement en face des induits, p. ex. dynamos de bicyclette du type moyeu
15.
Method of manufacturing an integral profile monolithic wing structure
A method of manufacturing a wing structure includes laying a plurality of layers of preimpregnated material on a first mould half and on a second mold half so as to form a first fresh skin and a second fresh skin of the wing structure. A plurality of layers of preimpregnated material are laid in succession on a shaped apparatus to form a fresh leading edge skin of the wing structure. Fresh spars of preimpregnated material are formed. A wedgelike body of expanded plastics material is formed, this body being designed to be interposed between the first and second skins at the trailing edge of the wing structure. The fresh spars are positioned in a coordinated way on the first fresh skin, removable support members also positioned next to the spars. The second mold half is turned over on to the first mold half so as to position the second fresh skin on the spars and the supports, to produce a fresh wing structure. The fresh wing structure is subjected to a polymerization cycle, using a vacuum bag.
B29C 65/70 - Assemblage d'éléments préformésAppareils à cet effet par moulage
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 65/00 - Assemblage d'éléments préformésAppareils à cet effet
B29C 70/54 - Parties constitutives, détails ou accessoiresOpérations auxiliaires
B64C 3/24 - Structures moulées ou venues de fonderie
B29C 35/08 - Chauffage ou durcissement, p. ex. réticulation ou vulcanisation utilisant l'énergie ondulatoire ou un rayonnement corpusculaire
B29K 63/00 - Utilisation de résines époxy comme matière de moulage
B29K 105/24 - Présentation, forme ou état de la matière moulée réticulée ou vulcanisée
A method of manufacturing a curved element made of composite material includes: preparing at least one dry, flat reinforcing layer with curved fibers. A resin film is combined with the dry, flat reinforcing layer, and heat and pressure are applied in controlled manner to bring about the infusion of the resin into the reinforcing layer and to obtain at least one layer of pre-infused material. At least one prepreg layer is prepared with straight fibers impregnated with resin compatible with the resin of the pre-infused material. The layer of pre-infused material and the prepreg layer are superimposed on one another to obtain a layered structure. The layered structure, arranged on a shaped support tool is subjected to a polymerization cycle to obtain the curved element.
B32B 5/08 - 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 les fibres ou filaments d'une couche étant disposés d'une certaine manière ou étant faits de substances différentes
C09J 5/02 - Procédés de collage en généralProcédés de collage non prévus ailleurs, p. ex. relatifs aux amorces comprenant un traitement préalable des surfaces à joindre
17.
Braking system for the undercarriage of an aircraft
A braking system for an aircraft provided with undercarriage, wherein an axial-flux reversible electric machine is set between the wheel and the frame of the undercarriage; current-dissipating resistors are provided, which can be connected to the windings of the axial-flux reversible electric machine during rotation of said wheel for dissipating by the Joule effect the induced currents generated by the axial-flux electric machine, which behaves as current generator, and producing a braking effect that slows down the movement of the wheel, thus exerting a braking action.
H02P 3/14 - Dispositions pour l'arrêt ou le ralentissement de moteurs, génératrices électriques ou de convertisseurs dynamo-électriques pour arrêter ou ralentir individuellement un moteur dynamo-électrique ou un convertisseur dynamo-électrique pour arrêter ou ralentir un moteur à courant continu par freinage en récupération
Gripping claws and pairs of arched angular profiles are arranged along the perimeter of a cylindrical surface segment so as to grip the edges of a fuselage panel, closing the opening of a pressurizable chamber.
G01M 5/00 - Examen de l'élasticité des structures ou ouvrages, p. ex. fléchissement de ponts ou d'ailes d'avions
G01N 3/08 - Recherche des propriétés mécaniques des matériaux solides par application d'une contrainte mécanique par application d'efforts permanents de traction ou de compression
G01N 3/10 - Recherche des propriétés mécaniques des matériaux solides par application d'une contrainte mécanique par application d'efforts permanents de traction ou de compression engendrés par pression pneumatique ou hydraulique
19.
Curing method and apparatus for manufacturing beams of composite material with a J-shaped cross-section
In order to manufacture beams of composite material with a J-shaped cross-section, a curing apparatus includes a bar supported parallel to a table by two end supports. A J-shaped beam of uncured composite material is prepared and arranged on the apparatus, positioning the bottom flange of the beam so that it faces the table and resting the web and the upper flange against two respective sides of the bar. The beam is covered with a vacuum bag and pressure and heat are applied inside an autoclave in order to cure the resin in the beam.
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
20.
Method for increasing the lift of aerodynamic surfaces and for reducing the drag
A jet of air is impelled on to the upper surface of a flap in order to increase its lift. Part of the air in this air jet is drawn, through air intakes, from the air stream flowing over an upper surface of the fixed part of the wing, located upstream of the flap. The air jet drawn in by suction by the air intakes is reinforced by a jet of compressed air blown through a passage which opens immediately downstream of the air intakes. This creates a combined jet of the air sucked in and the blown jet, which is ejected on to the upper surface of the flap through outlet apertures located on the rear edge of the fixed part of the wing.
B64C 21/08 - 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 réglables
21.
PROCEDURE FOR THE PROGNOSTIC OF A STRUCTURE SUBJECT TO LOADS
A method for prognostics of a structure subject to loads, particularly an aircraft structure, is disclosed, which comprises: - detecting the state (strains) of the structure is a plurality of primary points and additional points; - determining the loads acting on the structure associated with the state detected in the primary points; - estimating, based on the determined loads, the state of the structure in the additional points; and - comparing the estimated state of the structure with the state detected in the additional points; whereby a soundness state of the structure is assessed if the estimated and detected values of the state quantity are in agreement, or a defectiveness state of the structure if such values differ.
A method of manufacturing a Z-section component from composite material uses a mold having a convex mold portion and a concave mold portion. The method includes the preparation of a vacuum bag for a polymerization cycle, including the covering the fresh component with a layer of peel ply formed from a plurality of strips of peel ply and fixing the layer of peel ply perimetrically to the mold using an adhesive tape. A line of sealant is positioned perimetrically above the adhesive tape around the fresh component and a separator film is positioned above the layer of peel ply so as to cover the layer of peel ply and the perimetric line of sealant. A ventilation textile is placed perimetrically on the mold, the textile having an aperture which is positioned so as to leave uncovered an underlying part substantially coinciding with the fresh component. A vacuum bag is applied for the polymerization cycle.
B29C 70/00 - 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
B29C 70/24 - Façonnage de matières composites, c.-à-d. de matières plastiques comprenant des renforcements, des matières de remplissage ou des parties préformées, p. ex. des inserts comprenant uniquement des renforcements, p. ex. matières plastiques auto-renforçantes des renforcements fibreux uniquement caractérisées par la structure des renforcements fibreux utilisant des fibres de grande longueur, ou des fibres continues orientées dans au moins trois directions formant une structure tridimensionnelle
23.
Process for monitoring the curing reaction of a polymeric matrix of a composite material
tracing the current intensity value measured by the amperemeter, which is correlated to the progress of the curing reaction of the polymeric matrix, so as to control said progress.
B32B 37/14 - Procédés ou dispositifs pour la stratification, p. ex. par polymérisation ou par liaison à l'aide d'ultrasons caractérisés par les propriétés des couches
24.
Structural element for covering an elongate gap on an aerodynamic surface of an aircraft
A covering structural element is adapted to close an elongate gap provided on an aerodynamic surface of an aircraft. Such an element has a strip-shaped body made of metal material, including a fixing portion, adapted to be fixed along one of the longitudinal borders of the elongate gap; a sliding portion adapted to urge in a sliding manner on the other of the longitudinal borders of the strip-shaped gap; and a connection portion, connecting the sliding portion to the fixing portion, the thickness of which is so sized as to allow, in use, a controlled elastic bending of the structural covering element. The covering structural element has a profile so sized as to be tapered at the transition from the fixing portion to the connection portion and from the sliding portion to the connection portion, the covering structural element having a smooth surface on the side intended to face away from the elongate gap.
A test arrangement for a laser threats identifying system of an aircraft is described, which comprises optical detecting means (10), adapted to pick up threat light beams (B) impinging on the aircraft (12) from a plurality of surrounding space sectors, and a threat warning unit (30), adapted to receive a plurality of actual optical signals indicative of at least one of the threat beams (B) through a plurality of optical channels (20) related to respective beam incidence directions, and arranged for comparing the actual signals with a predetermined library of reference optical signals representing known threats. The test arrangement includes a light emitting source (L) arranged for selectively generating a plurality of predetermined optical signals for simulating virtual threats (S1-Sn), and a plurality of optical guides (F1-Fn) for the simulation signals (S1-Sn), directly coupled with the source (L) and adapted to be connected to the aforementioned optical channels (20_1- 20_n) for selectively stimulating the threat warning unit (30).
A dome structure has dimensions such as to house the cockpit of an aircraft. An ordered arrangement of light-emitting panels (10), able to be switched on or off selectively, forms at least a part of the inner vault of the dome. A floodlight (16) is mounted on a movable support arm (17) such that it can be selectively positioned around or above the cockpit and directed so as to project a beam of light onto the cockpit. Preferably a part of the inner vault of the dome consists of an ordered arrangement of reflective panels (11).
A method for manufacturing a recycled prepreg material (DW) in strip form, composed of fibre sections embedded in a resin matrix, is described. According to the method, a charge of flat scraps (S) from a prepreg starting material is supplied, recording the overall area of the scraps. Then the scraps are fragmented by means of cutting so as to obtain cut fragments (S2) of predetermined size. A strip of backing material (SW) and a strip of protective material (PW) are supplied. The cut fragments are then distributed in a random manner on the strip of backing material, the feeding speed of the strip of backing material being adjusted depending on the recorded area of the input scraps, so that the cut fragments form a substantially homogeneous layer. The strip of protective material is then arranged over the cut fragments distributed on the strip of backing material, and the whole assembly is then compacted so as to form a strip of recycled prepreg material (DW).
B29B 17/00 - Récupération de matières plastiques ou d'autres constituants des déchets contenant des matières plastiques
B29C 70/50 - Façonnage ou imprégnation par compression pour la fabrication d'objets de longueur indéfinie, p. ex. de "prepregs", de préimprégnés [SMC] ou de nappes multiaxiales [XMC]
28.
ELECTRONIC PROCESSING SYSTEM FOR AID TO UNMANNED NAVIGATION IN PARTICULAR UNMANNED AIR NAVIGATION
The present invention relates to an electronic processing system for aid to unmanned navigation, in particular unmanned air navigation, comprising one or more processing nodes (1, 2), each connected to a respective system controller (4, 5), in turn connected to memory means (8, 9, 10, 11, 12, 13) through a first communication channel or bus (6, 7), characterised in that the system controller (4, 5) of each one of said one or more nodes (1, 2) is connected, through a respective PCI bus (23, 24), to a FPGA device (3) incorporating first I/O interface means (31, 32, 33), the FPGA device (3) further comprising, for each one of said one or more nodes (1, 2), a PCI communication unit (301) connected to the corresponding system controller (4, 5), and first means (303, 304, 305, 306, 312) of control between the respective PCI bus (23, 24) and said first I/O interface means (31, 32, 33).
G06F 13/16 - Gestion de demandes d'interconnexion ou de transfert pour l'accès au bus de mémoire
G06F 13/20 - Gestion de demandes d'interconnexion ou de transfert pour l'accès au bus d'entrée/sortie
G06F 15/17 - Communication entre processeurs utilisant une connexion de type entrée/sortie, p. ex. canal, point d'accès entrée/sortie
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
29.
METHOD FOR MANUFACTURING AN ELONGATED STRUCTURAL ELEMENT MADE OF COMPOSITE MATERIAL BY MEANS OF FORMING AND CURING IN AN AUTOCLAVE USING A VACUUM BAG
The invention relates to a method for manufacturing a long structural component (20') made of composite material by means of forming and curing in an autoclave using a vacuum bag. A plurality of prepreg layers (21) are laminated in succession on a surface. The laminate (20) thus obtained is positioned on a convex male portion of the mould (40). A low-friction separator film (30) is arranged between the laminate and the mould. A vacuum bag (50) comprising a ventilation layer (52), having a substantially invariable set thickness, and a high- stretch vacuum bag film (53) which is substantially taut are prepared. The laminate on the mould (12) is subject to a temperature, vacuum and pressure cycle programmed to cause polymerization of the prepreg resin and also comprising a forming step able to cause adaptation of the form of the laminate (20) to the convex male portion (41) of the mould (40). The forming step immediately precedes polymerization of the prepreg resin.
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 70/44 - 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
B29D 99/00 - Matière non prévue dans les autres groupes de la présente sous-classe
30.
A COMPOSITE MATERIAL WHICH IS SELF-REPAIRING EVEN AT LOW TEMPERATURE
The composite material comprises a thermosetting polymer matrix in which a ring-opening metathesis reaction catalyst, and microcapsules containing a reactive monomer which can polymerize as a result of a ring-opening metathesis reaction and subsequently cross-link, are dispersed. The reactive monomer is 5-ethylidene-2-norbornene and the catalyst is preferably selected from the group constituted by Grubbs and Hoveyda-Grubbs catalysts.
B29C 73/16 - Dispositions ou agents d'autoréparation ou d'auto-obturation des perforations
B29C 73/22 - Dispositions ou agents d'autoréparation ou d'auto-obturation des perforations l'objet comportant des éléments comprenant une composition de scellement, p. ex. une poudre qui se libère quand l'objet est endommagé
C08L 51/08 - Compositions contenant des polymères greffés dans lesquels le composant greffé est obtenu par des réactions faisant intervenir uniquement des liaisons non saturées carbone-carboneCompositions contenant des dérivés de tels polymères greffés sur des composés macromoléculaires obtenus autrement que par des réactions faisant intervenir uniquement des liaisons non saturées carbone-carbone
C08L 51/00 - Compositions contenant des polymères greffés dans lesquels le composant greffé est obtenu par des réactions faisant intervenir uniquement des liaisons non saturées carbone-carboneCompositions contenant des dérivés de tels polymères
B01J 13/18 - Polymérisation in situ où tous les réactifs sont présents dans la même phase
31.
EPOXY RESIN BASED COMPOSITION AND METHOD FOR THE CURING THEREOF
The composition comprises at least one epoxy resin, carbon nanotubes in a quantity of between 0.1 and 10 parts by weight per 100 parts of epoxy resin and at least one curing agent of the epoxy resin in a quantity of between 5 and 50 parts by weight per 100 parts of epoxy resin. The method of curing said composition comprises the phases of mixing the above-stated ingredients, and of heating the resultant mixture to a temperature of between 100 and 250°C.
An aircraft chaff dispenser (10) comprises an elongated hollow housing (12) intended to be fixed to the structure of the aircraft so as to be oriented in the longitudinal direction of the aircraft. The housing (12) has a pair of side walls (14) and the front of each side wall (14) is provided with a pair of lateral air intakes (16) each comprising a circular through-hole (18) with a diameter d and a fence (20) located behind the hole (18) in the longitudinal direction, or in the direction of travel, of the aircraft at a distance 1 from the centre of the said hole and having a shape in the form of a horizontally lying V with its vertex directed away from the hole (18). The diameter d of the hole (18) is between 8 and 12 mm. The ratio h/1 between the height h of the fence (20) at the vertex of the V and the distance 1 is between 0.8 and 1, while the ratio h/d between the height h and the diameter d is between 1.5 and 2.
F41H 11/02 - Installations ou systèmes de défense anti-aérienne ou antimissiles
F42B 12/48 - Projectiles ou mines caractérisés par la charge militaire, l'effet recherché ou le matériau caractérisés par la nature de la charge militaire ou par l'effet recherché pour libérer des matériaux, des corps ou des particulesProjectiles ou mines caractérisés par la charge militaire, l'effet recherché ou le matériau caractérisés par la nature de la charge militaire ou par l'effet recherché pour produire une réaction chimique ou physiqueProjectiles ou mines caractérisés par la charge militaire, l'effet recherché ou le matériau caractérisés par la nature de la charge militaire ou par l'effet recherché pour la signalisation pour libérer des gaz, des vapeurs, des poudres ou des substances qui sont chimiquement réactifs fumigènes
F42B 12/70 - Projectiles ou mines caractérisés par la charge militaire, l'effet recherché ou le matériau caractérisés par la nature de la charge militaire ou par l'effet recherché pour libérer des matériaux, des corps ou des particulesProjectiles ou mines caractérisés par la charge militaire, l'effet recherché ou le matériau caractérisés par la nature de la charge militaire ou par l'effet recherché pour produire une réaction chimique ou physiqueProjectiles ou mines caractérisés par la charge militaire, l'effet recherché ou le matériau caractérisés par la nature de la charge militaire ou par l'effet recherché pour la signalisation pour la libération de corps solides individuels pour la libération de paillettes antiradar ou de matériaux à émission infrarouge
B64D 29/00 - Nacelles, carénages ou capotages des groupes moteurs
33.
APPARATUS FOR THE INFUSION OF RESIN INTO A PREFORM IN A CLOSED MOULD
A tool (1; 101) for the infusion of a resin into a preform (P; A, B, C D) made of fibre material comprises a mould (3; 103) which can be closed around the preform and in the body of which at least one inlet duct (5; 105) is formed to allow resin to be injected into the mould so that the resin can be infused into the preform. At least one reservoir (10; 108, 109), which can contain the resin, is also formed in the body of the mould and is connected to the at least one inlet duct, wherein the mould can be inserted in an autoclave and the reservoir is configured to permit the transfer of the resin from the reservoir to the inlet duct under the effect of the temperature and of the pressure that are produced in the autoclave, thus allowing the resin to be injected into the mould.
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 70/48 - 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" avec une imprégnation des renforcements dans le moule fermé, p. ex. moulage par transfert de résine [RTM]
B29C 70/54 - Parties constitutives, détails ou accessoiresOpérations auxiliaires
34.
A METHOD FOR APPLYING A VACUUM BAG AROUND A FUSELAGE BARREL MADE OF COMPOSITE MATERIAL TO BE POLYMERIZED
A vacuum bag is applied around a fuselage barrel (11) made of composite material to be polymerized, formed by means of lamination on the outer surface of a mandrel (10) having the form of a solid of rotation about a longitudinal axis (x). A bag material in the form of a sheet (30) having a transverse width corresponding to the longitudinal length of the fuselage barrel (11) is provided alongside the mandrel. A first transverse end portion (30a) of the sheet is fastened or sealed on the outer surface of the barrel (11) or the mandrel (10). Then the mandrel is rotated around the axis (x), so as to wrap the sheet (30) about the barrel (11). While the mandrel (10) rotates, the opposite axial end edges (30d) of the sheet (30) are sealed on the mandrel (10). Finally, a second transverse end portion (30b) of the sheet is sealed on the outer surface of the barrel (11) or the mandrel.
B29C 70/32 - 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 sur un moule, un gabarit ou un noyau rotatifs
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
B65B 11/04 - Enveloppement d'objets ou de quantités de matériaux sans changer leur position durant l'opération, p. ex. dans des moules avec des plieurs à charnières en faisant tourner les objets
35.
APPARATUS FOR THE MANUFACTURE OF STRUCTURAL ELEMENTS MADE OF COMPOSITE MATERIAL
Electrical resistors (12) are incorporated in a forming tool (10) having an upper forming surface (11) on which to deposit a superimposed arrangement of reinforcing- fibre sheets (C).A vacuum bag (V) is placed on the reinforcing-fibre sheets. An openable cover (13) is arranged on the tool to define a hermetically sealed space (22) therewith. A vacuum pump (16) withdraws air from the forming surface (11) and an inlet line (18) admits pressurized air to the space (22) through the cover (13). Optional resin-supply ducts (20) open in the forming surface (11).
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
The inner structure (20) of a wing is first fixed on the top surface (11) of the bottom panel (10). The inner structure and the top panel (12) are retained separately in the respective forms which they must assume in accordance with a predetermined wing profile. The top surface (21) of the inner structure (20) and the bottom surface (14) of the top panel (12) are scanned. The three-dimensional digital images of the scanned surfaces are processed, so as to generate a three-dimensional mathematical model representing the distances between the scanned surfaces. On the basis of the mathematical model one or more inserts (70) with a variable thickness corresponding to the distances between the scanned surfaces are manufactured. The inserts are then arranged between these surfaces and finally the top panel (12) is fixed to the structure (20), thus obtaining the predetermined wing profile.
B64C 3/26 - Construction, forme ou fixation des revêtements distincts, p. ex. panneaux
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
37.
A METHOD OF MANUFACTURING A CURVED STRUCTURAL ELEMENT MADE OF COMPOSITE MATERIAL AND HAVING A COMPLEX, OPEN CROSS-SECTION
A method of manufacturing a curved structural element made of composite material and having a complex, open cross-section is described, in which the structural element is formed by the assembly of components made of composite material. First of all a plurality of flat, fresh components (10, 20, 30; 110, 120, 130) are prepared, each component being constituted by a flat layer of curved fibres previously infused with resin, combined with a pre-impregnated layer with straight fibres. Hot-forming of the flat, raw components is then performed. The hot-formed, fresh components are then assembled in accordance with a predetermined sequence on a polymerization tool. The tool comprises a shaped, inflatable device (42; 42'; 42') astride which a C-shaped raw component is deposited. Finally, the fresh components assembled on the tool are subjected to a polymerization cycle in an autoclave. The inflatable device is inflated by means of the pressure produced in the autoclave in order to apply a predetermined pressure from the inside of the C-shaped fresh component.
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 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 70/44 - 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
38.
A METHOD OF MANUFACTURING A CURVED ELEMENT MADE OF COMPOSITE MATERIAL
A method of manufacturing a curved element made of composite material comprises the following steps: a) preparing at least one dry, flat reinforcing layer (1) with curved fibres, b) combining a resin film (2) with the dry, flat reinforcing layer, and applying heat and pressure in controlled manner so as to bring about the infusion of the resin into the reinforcing layer and to obtain at least one layer of pre-infused material (Y), c) preparing at least one prepreg layer (31, 32) with straight fibres impregnated with resin compatible with the resin of the pre-infused material, d) superimposing the layer of pre-infused material and the prepreg layer on one another so as to obtain a layered structure (1'), and e) subjecting the layered structure, arranged on a shaped support tool (30), to a polymerization cycle so as to obtain the curved element.
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 70/50 - Façonnage ou imprégnation par compression pour la fabrication d'objets de longueur indéfinie, p. ex. de "prepregs", de préimprégnés [SMC] ou de nappes multiaxiales [XMC]
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
39.
A METHOD OF MANUFACTURING AN INTEGRAL PROFILE MONOLITHIC WING STRUCTURE
A method of manufacturing a wing structure (10) is described. A plurality of layers of preimpregnated material are laid on a first mould half (51) and on a second mould half (52) so as to form a first fresh skin (22) and a second fresh skin (21) of the wing structure. A plurality of layers of preimpregnated material are laid in succession on a shaped apparatus (80) so as to form a fresh leading edge skin (23) of the wing structure. Fresh spars (30) of preimpregnated material are formed. A wedgelike body (40) of expanded plastics material is formed, this body being designed to be interposed between the first and second skins at the trailing edge of the wing structure. The fresh spars are positioned in a coordinated way on the first fresh skin, removable support members (100) also being positioned next to the spars. The second mould half is turned over on to the first mould half so as to position the second fresh skin on the spars and the support means, so as to produce a fresh wing structure. The fresh wing structure is subjected to a polymerization cycle, using a vacuum bag.
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
A jet of air is impelled on to the upper surface (22) of a flap (20) in order to increase its lift. Part of the air in this air jet is drawn, through air intakes (41), from the air stream flowing over an upper surface (11) of the fixed part (10) of the wing, located upstream of the flap. The air jet drawn in by suction by the air intakes (41) is reinforced by a jet of compressed air blown through a passage (30) which opens immediately downstream of the air intakes (41). This creates a combined jet, comprising the air sucked in and the blown jet, which is ejected on to the upper surface (22) of the flap through outlet apertures (44) located on the rear edge of the fixed part of the wing.
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
41.
METHOD AND EQUIPMENT FOR FORMING AND ASSEMBLING UNCURED SPARS FOR THE HORIZONTAL STABILIZERS OF AIRCRAFT
H-beam carbon-resin spars for the horizontal stabilizers of aircraft are formed by using forming devices (60) each of which comprises an elongate core (61) of rectangular cross section fixed securely to a flat plate (62) which extends around the whole of the core (61). An overhead travelling crane (10, 11) can run in a longitudinal direction and has pick-up means (16) which are vertically movable and can be turned over about a transverse axis. A flat section to be formed is placed on a first upward-facing core; the section and the first core are transferred together into a hot forming apparatus (20, 21), and a vacuum and heat are applied to deform the section on to the core, thus producing a first C-section (14). A second C-section (13) is produced in a similar way. This is turned over, using the pick-up means (16) of the overhead travelling crane, and is placed on top of the first section (14), so as to bring the webs of the two sections together in an H-beam configuration.
B29C 51/10 - Formage par une différence de pression, p. ex. sous vide
B29C 69/00 - Combinaisons de techniques de façonnage non prévues dans un seul des groupes principaux , p. ex. associations de techniques de moulage et d'assemblageAppareils à cet effet
B29D 99/00 - Matière non prévue dans les autres groupes de la présente sous-classe
In order to manufacture beams of composite material with a J-shaped cross-section, a curing apparatus comprising a bar (20) supported parallel to a table (50) by means of two end supports (30) is prepared. A J-shaped beam (A) of uncured composite material is prepared and arranged on the apparatus (10), positioning the bottom flange (D) of the beam so that it faces the table (50) and resting the web (C) and the upper flange (B) against two respective sides (22, 21) of the bar (20). The beam (A) is covered with a vacuum bag (V) and pressure and heat are applied inside an autoclave in order to cure the resin in the beam.
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
43.
METHOD OF MANUFACTURING A Z-SECTION COMPONENT FROM COMPOSITE MATERIAL
What is described is a method of manufacturing a Z -section component from composite material, using a mould (12) having a convex mould portion (12a)' and a concave mould portion (12b). The method includes the preparation of a vacuum bag (90) for a polymerization cycle, comprising the following stages: covering the fresh component' with a layer of peel ply (60) formed from a plurality of strips of peel ply (61a, 61b, 61c); fixing the layer of peel ply perimetrically to the mould, using an adhesive tape (65); positioning a line of sealant (66) perimetrically above 'the adhesive tape around the fresh component; positioning a separator film (70) above the layer of peel ply so as to cover the layer of peel ply and the perimetric line of sealant; positioning a ventilation textile (80) perimetrically on the mould (12), this textile having an aperture (81) which is positioned so as to leave uncovered an underlying part substantially coinciding with the fresh component; and applying the vacuum bag for the polymerization cycle. The method includes also a preliminary compaction of successively deposited layers of preimpregnated material.
B29C 70/44 - Façonnage ou imprégnation par compression pour la fabrication d'objets de longueur définie, c.-à-d. d'objets distincts utilisant une pression isostatique, p. ex. moulage par différence de pression, avec un sac à vide, dans un autoclave ou avec un caoutchouc expansible
B29C 70/54 - Parties constitutives, détails ou accessoiresOpérations auxiliaires
44.
A METHOD AND A SYSTEM FOR ESTIMATING THE IMPACT AREA OF A MILITARY LOAD LAUNCHED FROM AN AIRCRAFT
A system and a method are here described for the estimation of the impact area of a ballistic or smart load, that can be launched from an aircraft as a function of data or signals indicative of the aircraft flight conditions upon release of the load and of predetermined impact conditions on the target, characterized by the estimation of a polygonal impact area defined by the coordinates of a central point and of a predetermined number of vertices by means of a plurality of corresponding neural networks.
An article (1) of composite material includes a plurality of plies of material (10) consoli¬ dated through the application of pressure and heating, in which each material ply is made by a resin matrix reinforced with fibre material. The article includes a heating electrical resistance (20) and temperature sensing devices (30) embedded in the composite material, which are respectively placed in at least one interface zone (11, 13) between the material plies and are suitable to allow a temperature control of the article in service.
B32B 5/02 - Produits stratifiés caractérisés par l'hétérogénéité ou la structure physique d'une des couches caractérisés par les caractéristiques de structure d'une couche comprenant des fibres ou des filaments
B32B 17/04 - Produits stratifiés composés essentiellement d'une feuille de verre ou de fibres de verre, de scorie ou d'une substance similaire sous forme de fibres ou filaments collés ou enrobés dans une substance plastique
B64D 15/12 - Dégivrage ou antigivre des surfaces externes des aéronefs par chauffage électrique
46.
PRE-IMPREGNATED MATERIAL WITH SEMI-CRYSTALLINE MATRIX AND AMORPHOUS SURFACE LAYER
A pre-impregnated material (1) comprises a resin matrix reinforced with a fibre material. The matrix comprises a semi-crystalline layer (10) based on semi-crystalline thermoplastic resin having a melting point Tf, on at least one side of which there is an amorphous surface layer (22, 23) based on amorphous thermoplastic resin having a glass transition temperature Tg, in which the glass transition temperature Tg of the amorphous thermoplastic resin is below the melting point Tf of the semi-crystalline thermoplastic resin.
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 5/04 - Renforcement des composés macromoléculaires avec des matériaux fibreux en vrac ou en nappes
47.
SYSTEM FOR ON-GROUND SIMULATION OF THE AMBIENT LIGHTING CONDITIONS IN THE COCKPIT OF AN AIRCRAFT DURING FLIGHT
A dome structure has dimensions such as to house the cockpit of an aircraft. An ordered arrangement of light-emitting panels (10), able to be switched on or off selectively, forms at least a part of the inner vault of the dome. A floodlight (16) is mounted on a movable support arm (17) such that it can be selectively positioned around or above the cockpit and directed so as to project a beam of light onto the cockpit. Preferably a part of the inner vault of the dome consists of an ordered arrangement of reflective panels (11).
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
F21S 8/00 - Dispositifs d'éclairage destinés à des installations fixes
48.
METHOD, PLANT AND APPARATUS FOR MAKING PARTS MADE OF COMPOSITE MATERIAL
The invention concerns a plant for manufacturing parts made of composite material, in particular sections for an aircraft fuselage, comprising at least a compaction station in which, in operation, there are provided a mandrel (20) coated of composite material to be compacted and transport means (30, 35, 36) arranged to transport at least one compaction device (37) on said composite material. The transport means (30, 36, 35) is associated with at least one sling (35) having at least one strip of porous material that, in operation, is in direct contact with the compaction device (37), and said sling is configured to transport the compaction device (37) onto said composite material (21) through application of a vacuum source (54a) at least to the strip of porous material (57). The invention also concerns a method of and an apparatus for manufacturing parts made of composite material.
The tool (1) according to the invention is equipped with cutting inserts (5) made of polycrystalline diamond and with washing channels cooling the tool from the inside and discharging, through outlet holes (15), jets of compressed air that remove the highly abrasive powders produced during machining from the cutting areas. In this manner, the tool undergoes less abrasion and anyway it can be sufficiently cooled. The particular choice of the material of the cutting inserts makes the tool more abrasion resistant, while conferring it in the whole a longer operating life. The invention also concerns a method of milling composite materials.
The present invention relates to a system to manufacture composite material parts comprising a supporting mandrel having at least one compacting zone (12) configured to contain at least one composite material element (21) to be compacted by applying a certain degree of vacuum. The system comprises also at least one compacting equipment (30) comprising a frame (31) having a plurality of interconnected arms along a predetermined perimeter, at least one vacuum bag (35) attached to a side of the frame (31) along its perimeter and configured to compact the element (21), at least one porous material (33) attached to the vacuum bag (25) along the frame's perimeter and configured to adhere in a removable way to the compacting zone (12) and to impede the air influx during the compacting of element (21). The invention also relates to a compacting equipment and to a method to manufacture composite material parts.
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
51.
METHOD, APPARATUS AND PLANT FOR MANUFACTURING SHELL STRUCTURES
According to the invention, a shell handling carriage (19) is provided with grippers (194) which grip the end edges of a shell (2) made of composite material still fixed to a molding drum (11). An expeller strut (13) prevents the drum (11) from moving while the carriage (19) translating 5 removes the shell (2) from the drum (11). The shell (2) is then transported by the carriage (19) to a working station in which robots rivet the transversal ribs on it. The transversal ribs reach the robot working position orderly arranged on a self-moving rib store, which is inserted in the shell (2) itself.
B64C 1/00 - FuselagesCaractéristiques structurales communes aux fuselages, voilures, surfaces stabilisatrices ou organes apparentés
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
52.
APPARATUS AND A METHOD FOR FABRICATING A FUSELAGE SECTION
.Method and apparatus for fabricating a fuselage section by the automatic deposition of fibre tapes impregnated with resin on an outer surface of a mandrel composed of radially retrectable sectors.
B29C 33/48 - 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
B29C 70/32 - 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 sur un moule, un gabarit ou un noyau rotatifs
B29C 70/38 - Empilage automatisé, p. ex. utilisant des robots, par application de filaments selon des modèles prédéterminés
A method for tracking the manufacture of a complex product from a plurality of components is described. The complex product and the component materials are sensitive to one or more monitoring parameters. The method comprises the steps of : associating a radio frequency identification device with each of the components, the identification device storing updatable data on the accumulated life which are dependent on the monitoring parameters, and which indicate the ageing of the component; reading the identification devices in a contactless way by means of radio frequency so as to retrieve the accumulated life data of the components; combining the component materials according to a predetermined manufacturing procedure so as to obtain the complex product; associating a radio frequency identification device with the complex product, the device being capable of storing updatable accumulated life data which are dependent on the monitoring parameters, and which indicate the ageing of the complex product; comparing with each other the accumulated life data retrieved for the corresponding components according to a programmed algorithm', so as to make a selection among the accumulated life data of the components; and writing the selected accumulated life data in a contactless way, by means of radio frequency, to the identification device associated with the product. The selected accumulated life data are stored as the initial accumulated life data of the complex product .
brevets
