Patents Assigned to EADS FRANCE
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Publication number: 20110036495Abstract: To produce a complex structure made of a composite, with assembled individual parts, a method includes the steps of: producing individual parts; producing assembly components, to ensure structural bonds between the individual parts, from fibers impregnated with a resin capable of curing by polymerization, comprising fins attached to a core that determine grooves, in order to receive edges, of the individual parts, subjected to a partial thermal cure to partially polymerize the resin and give the components a dimensional stability and thermoplastic properties; positioning of the individual parts and assembly components; raising the temperature to a thermoplastic forming temperature and applying pressure P in order to apply the fins to faces of the individual parts; and carrying out a complete thermal cure for polymerization of the resin of the assembly components.Type: ApplicationFiled: August 5, 2008Publication date: February 17, 2011Applicant: European Aeronautic Defence and Space Company EADS FranceInventor: Jacques Cinquin
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Publication number: 20100289501Abstract: The behavior of a component subjected to pulsed laser radiation is measured. The polarization value, frequency, and temperature (or other operating conditions) to which the component is sensitive are determined by detecting a temporary or permanent fault in the operation of the component. If necessary, the parasitic currents generated are prevented from destroying the tested component at the time of testing. A susceptibility of the component to energetic interactions and the preferred operating conditions for the component are deduced.Type: ApplicationFiled: September 5, 2008Publication date: November 18, 2010Applicant: European Aeronautic Defence and Space Company EADS FranceInventors: Nadine Buard, Florent Miller, Patrick Heins, Thierry Carriere
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Publication number: 20100288820Abstract: The invention relates to a double shouldered welding device for the friction stir welding of parts, in which at least one shoulder has two concentric rings providing two plane concentric bearing surfaces, the rings being arranged so that the smaller-diameter ring is capable of compressing the stirred material of the parts to be welded during advance of the welding device and so that the larger-diameter ring is capable of forming a sink-in stop for the smaller-diameter ring. The invention also relates to a method of friction stir welding by means of the welding device according to the invention, in which said device is force-driven.Type: ApplicationFiled: September 10, 2008Publication date: November 18, 2010Applicant: European Aeronautic Defence And Space Company EADS FranceInventors: Daniel Aliaga, Baptiste Guerin, Francois Marie
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Publication number: 20100278586Abstract: A connecting rod is composed of two or more assembled shells made of a composite, open over the entire length of the connecting rod. The shells incorporate clevis joints for introducing stress at each of their ends. The shells are produced separately then assembled together to form a sealed section. Each shell is made from a material preimpregnated with long fibres. The production of each shell is simplified due to the overall shape of the shell as a simple curve, thus a shell may be produced industrially, for example, by thermoforming a flat composite preform. The two shells are assembled by simultaneous polymerization of the shells, by bonding, by welding, by riveting or any other assembly process or combination of assembly processes that are compatible with one another. The structural composite connecting rod obtained has very good mechanical properties, especially in compression, with a simple and economic production process.Type: ApplicationFiled: June 27, 2008Publication date: November 4, 2010Applicants: European Aeronautic Defence And Space Company EADS France, Composite Atlantic LimitedInventors: Frédérick Cavaliere, Maurice Guitton, Olivier Blanc, Claude Baril
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Publication number: 20100280785Abstract: To test a software application, a method submits an electronic board including a component implementing an application to a laser radiation generated in test equipment. The component is excited with laser pulses having very short durations distributed during complex operational phases of the component for running the application, and the reaction of the component and the application are observed.Type: ApplicationFiled: June 26, 2008Publication date: November 4, 2010Applicant: European Aeronautic Defence And Space Company EADS FranceInventors: Nadine Buard, Florent Miller, Antonin Bougerol, Patrick Heins, Thierry Carriere
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Publication number: 20100266836Abstract: The present invention relates to a structure comprising: at least one mesostructured layer prepared by the sol-gel route from at least one specific molecular metallic precursor in the presence of an amphiphilic surfactant, and a metal substrate. It also relates to its process of preparation and to its use in the aeronautical or aerospace field.Type: ApplicationFiled: September 21, 2007Publication date: October 21, 2010Applicants: EURO. AERONAUTIC DEFENCE AND SPACE CO. EADS FRANCE, UNIVERSITE PARIS 6 PIERRE ET MARIE CURIE, CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE (CNRS)Inventors: Elisa Campazzi, Emmanuelle Lancelle-Beltran, Clement Sanchez
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Publication number: 20100252677Abstract: An aircraft includes a cabin in which at least part of the space is demarcated by trim panels and the cabin is provided with a system for the active control of ambient noise. Each trim panel is either an active panel including actuators powered by the active noise control system or a passive panel without such actuators. In addition, the trim panels of the cabin of the one type, either active or passive, are mechanically interchangeable with a panel of the other type, either passive or active, respectively. Power supply wiring for active panels is installed in the aircraft, this wiring being capable of powering all active panels which could be installed, whether said active panels are actually installed or whether interchangeable passive panels are installed. Finally, a power supply system for the active panels is installed in the aircraft and connected to the power supply wiring of the active panels.Type: ApplicationFiled: July 9, 2008Publication date: October 7, 2010Applicant: European Aeronautic Defence And Space Company EADS FranceInventor: Benoit Petitjean
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Patent number: 7766215Abstract: The invention relates to a process for the friction stir welding of two panels (20, 21), using a welding device (25) having a retractable pin (29), comprising the following steps: positioning the two panels (20, 21) so as to be in contact over an overlap region (24) and keeping them in the desired relative position after welding; bringing the welding device into contact with the upper panel at the start of the welded joint; longitudinally welding the two panels, by moving the welding device as far as the end of the welded joint; continuing to move the welding device (25) along a path extending beyond the end of the welded joint; and retracting the retractable pin (29) so as to prevent the appearance of a weld hole in a portion of the path of the welding device (25) extending beyond the end of the welded joint.Type: GrantFiled: April 3, 2007Date of Patent: August 3, 2010Assignee: European Aeronautic Defence and Space EADS FranceInventor: Francois Marie
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Publication number: 20100180424Abstract: The invention relates to a device for inserting and crimping a ring on an attachment rod in a hole, comprising a robot, a monitoring and control system and an end tool designed to crimp the ring on the rod. The end tool includes a crimping device and a ring installation device which are solidly connected to a fine-positioning device, by means of which the end tool is attached to an end element of the robot. A ring insertion subassembly of the ring installation device and a crimping nose of the crimping device can move on the end tool so as to be positioned alternatively on an axis of an attachment to be installed, with no controlled movement of the robot when the end tool has been pre-positioned.Type: ApplicationFiled: March 26, 2008Publication date: July 22, 2010Applicant: European Aeronautic Defence And Space Company EADS FranceInventor: Philippe Le Vacon
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Publication number: 20100147460Abstract: To manufacture a piece made of composite material with thermosetting matrix, at least one element of the piece is manufactured separately based on strips of fibers preimpregnated with thermosetting resin, which element is subject to a partial thermal curing, having the effect of partially polymerizing the resin of the first element, on the one hand, up to a stage in which the first element has acquired both a sufficient chemical stability to guarantee its storage at ambient temperature and a sufficient dimensional stability to ensure its handling and to guarantee its integrity during later manufacturing operations of the piece and, on the other hand, limited to a stage in which the material forming first element has thermoplastic properties making possible a plastic forming of the first element by raising its temperature at least locally.Type: ApplicationFiled: December 10, 2007Publication date: June 17, 2010Applicant: European Aeronautic Defence and Space Company EADS FranceInventor: Patrice Lefebure
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Patent number: 7736813Abstract: The invention concerns an electrochromic cell with emission controlled by electrodeposition under the action of a control voltage. The cell comprises the following flexible elements, superimposed and respectively in intimate contact: a first electrode (11) intended to be connected to a first potential of the control voltage, a first porous layer (12), formed of a mixture of PVDF-HFP, PEO and an activated carbon powder, a porous separator (13), formed of a mixture of PVDF-HFP and PEO, a second electrode (14) formed of a grid and connected to a second potential of the control voltage, a second porous layer (15), formed of a mixture of PVDF-HFP, PEO and carbon powder, an aqueous electrolytic solution containing a copper salt being contained in the first flexible layer (12), in the separator (13) and in the second flexible layer (15).Type: GrantFiled: December 19, 2005Date of Patent: June 15, 2010Assignee: European Aeronautic Defence and Space Company – EADS FranceInventors: Bruno Esmiller, Lionel Beluze, Jean-Claude Badot, Bruno Viana, Jean-Marie Tarascon
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Publication number: 20100096076Abstract: According to the invention, one or more thermoplastic sheets (NdT: “feuilles thermoplastique” in the original) (2) are applied on a flat or curved tool (13), and strips (NdT: “des bande” in the original) of a polymer are applied and pressed onto the sheets (2). They are maintained by suction pumps (8), the orifices (4) of which open into a closed volume or one substantially delimited by a sealing joint (3) and occupied by a draining fabric (7). The heating treatment concomitant to the deposition to harden or consolidate the prepreg softens the sheets (2), distorts them to the curvature of the tool (13) and incorporates them in the structure of the prepreg. Application to methods of draping parts with composite material.Type: ApplicationFiled: February 5, 2008Publication date: April 22, 2010Applicant: European Aeronautic Defence and Space Company-Eads FranceInventor: Eric Soccard
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Publication number: 20090309264Abstract: A stiffened panel made of a composite includes a skin and at least one stiffener having a more or less closed volume. In order for the fibres of the composite to be held in place during fibre deposition and during pressure application while the resin of the composite is being cured, a moulding core is placed between the fibres at the position of the more or less closed volume of the stiffener. The moulding core includes a flexible bladder filled with a granular solid material, the thermal expansion coefficient of which is close to that of the composite used to produce the stiffened panel. The pressure in the bladder is increased before the composite is cured, so as to compensate for the forces applied for compressing these fibres during production of the panel.Type: ApplicationFiled: March 20, 2007Publication date: December 17, 2009Applicant: EADS FRANCEInventor: Frederick Cavaliere
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Publication number: 20090309268Abstract: A method for producing a composite material part having a so-called non-strippable shape includes producing mold components, or cores, which are to be extracted from the part after the composite material has been cured. In a first step a core is produced from an elastomeric bladder the granular solid material and the bladder is depressurized. In a second step, after setting the core and the composite material the volume of the core is modified in a controlled manner for example by selecting the solid granular material based on its thermal expansion properties or by acting on the pressure in the bladder.Type: ApplicationFiled: March 20, 2007Publication date: December 17, 2009Applicant: EADS FRANCEInventors: Frederick Cavaliere, Maurice Guitton, Severine Guitton
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Publication number: 20090303141Abstract: To construct a reverberation chamber, a chamber provided with reflecting walls contains an antenna and a field stirrer which are placed opposite an object to be tested. By modifying an orientation of a main direction of irradiation from the antenna, a very large number of cavity modes are created inside the chamber, achieving the required variety of possible impingements on the object to be tested, such that the test carried out is as conclusive as possible and the least dependent possible on the dimensions and characteristics of the chamber.Type: ApplicationFiled: September 5, 2007Publication date: December 10, 2009Applicant: EADS FRANCEInventors: Frederik Kosdikian, Olivier Maurice, Olivier Urrea
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Publication number: 20090306908Abstract: A monitoring device of environmental parameter values of an environment surrounding a system. The device includes a sensor to these parameters, and includes a means of transmission, in real time, of each measurement to a processing unit. The processing unit is installed in the system and includes the means of filtering the transmitted measurements. This processing unit comprises the means for determining cycles from the measurements thus simplified as well as the means for calculation, in real time, of a length of consumed life of the system, from the thus determined cycles.Type: ApplicationFiled: January 23, 2007Publication date: December 10, 2009Applicants: EUROPEAN AERONAUTIC DEFENCE AND SPACE COMPANY EADS FRANCE, EADS CCR GROUPEMENT D'INTERET ECONOMIQUEInventors: Bruno Foucher, Vincent Rouet
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Publication number: 20090202815Abstract: The present invention relates to the use of a nanostructured material, as a protective coating for metallic surfaces, said nanostructured material comprising functionalized nano-building blocks and a polymer or hybrid organic/inorganic matrix. It also relates to a particular nanostructured material in which the matrix is prepared from at least three silicon alkoxides.Type: ApplicationFiled: April 12, 2007Publication date: August 13, 2009Applicants: EURO. AERONAUTIC DEFENCE AND SPACE CO. EADS FRANCE, UNIVERSITE PARIS 6 PIERRE ET MARIE CURIE, CENTRE NATIONAL DE LA RECHERCHE SCIENT. (CNRS)Inventors: Elisa Campazzi, Valerie Goletto, Clement Sanchez
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Publication number: 20090081433Abstract: The invention relates to a corrosion-resistant thin-film multilayer structure having a low wear rate and a low coefficient of friction, comprising 1 to 1000 periods, one period comprising 2 to 100 layers (A, B) based on carbon, silicon and hydrogen, and optionally a functional surface layer (FSL). The invention also relates to a component comprising the thin-film multilayer structure and to its method of deposition.Type: ApplicationFiled: January 30, 2007Publication date: March 26, 2009Applicant: EURO AERONAUTIC DEFENCE AND SPACE CO. EADS FRANCEInventors: Valerie Lucas, Mickael Joinet, Francis Teyssandier, Laurent Thomas
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Publication number: 20080210360Abstract: A method for assembling at least two rigid thermoplastic material based parts. The two parts are superposed to have at least one interface zone, wherein at least one of the two parts includes one or plural energy directors, protruding, situated in the interface zone. At least one excited ultrasonic source is brought into contact with one of the two parts, the ultrasonic source applying a compression effort to the two parts in a region of the interface zone located opposite the ultrasonic source. The ultrasonic source is continuously displaced at the interface zone to form a continuous welded joint by fusion of the thermoplastic material in the region positioned opposite the ultrasonic source. Such a method may find particular application for assembly of stratified parts.Type: ApplicationFiled: July 3, 2006Publication date: September 4, 2008Applicant: European Aeronautic Defence And Space Company - EADS FranceInventor: Eric Soccard
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Publication number: 20080170471Abstract: A standard non-destructive testing probe (4) may be coupled with a localization system (10) according to the invention so as to determine the position of the apparatus (4) on the surface to be analyzed (1) at any moment. The localization system (10) comprises an ultrasonic emitter (12) and two ultrasonic receivers (14, 16) coupled with means for determining the distance between the emitter (12) and the receivers (14, 16), each of the components being able to be moved freely relative to each other. The coupling between the emitter (12) and the probe (4) allows the position of the latter to be determined by triangulation. A localization and mapping method is also described.Type: ApplicationFiled: February 22, 2006Publication date: July 17, 2008Applicant: EUROPEAN AERONAUTIC DEFENCE AND SPACE COMPANY- EADS FRANCEInventors: Sebastien Rolet, Capucine Carpentier