Patent application number | Description | Published |
20110076431 | PREFORM INTENDED TO FORM A HOLLOW STRUCTURAL MECHANICAL PART, RESULTING PART AND METHOD FOR PRODUCING SAID PREFORM - The invention relates to a preform ( | 03-31-2011 |
20110081511 | METHOD FOR PRODUCING A PART COMPRISING A HOLLOW BODY MADE FROM A COMPOSITE MATERIAL - The invention relates to a method for producing a part comprising a hollow body made from a composite material, using preforms ( | 04-07-2011 |
20110290333 | METHOD FOR MANUFACTURING A STRUCTURE WITH CELLULAR CORES FOR A TURBOJET NACELLE - The invention relates to a method for manufacturing a structure with cellular cores ( | 12-01-2011 |
20120031038 | CELLULAR PANEL - The present invention relates to a cellular panel deployable from a compacted form to a deployed form, including, in the compacted form thereof, a plurality of consecutive sheets substantially parallel to one another and substantially perpendicular to an expansion direction, each sheet being discretely joined at a plurality of junction points with the following and/or preceding sheet, the junction points being substantially regularly spaced apart along the lines substantially parallel to the sheets and alternating with the preceding and/or following junction points, characterized in that, on at least one line parallel to the expansion direction, one or more junction points are excised or are not made and the portions of the sheets associated with said excised or unmade junction points are excised. | 02-09-2012 |
20120279635 | METHODS FOR PRODUCING A PART MADE FROM A COMPOSITE MATERIAL, OBTAINED BY DEPOSITING LAYERS OF REINFORCING FIBERS URGED ONTO A MANDREL - The invention relates to a method of fabricating a composite material part in which one or more layers of braided, or woven, or indeed draped reinforcing fibers are applied onto a mandrel having the general shape of a body of revolution. After one or more layers have been applied onto the mandrel, an operation is performed of winding at least one tie helically around and along the assembly constituted by the mandrel and each layer of reinforcing fibers that it carries, so as to press each layer of reinforcing fibers against the mandrel. The invention relates to fabricating composite material parts such as beams, connecting rods, or arms made out of carbon fibers. | 11-08-2012 |
20130108432 | AIRFLOW-STRAIGHTENING STRUCTURE FOR THE NACELLE OF AN AIRCRAFT ENGINE | 05-02-2013 |
20130121814 | TURBOJET ENGINE NACELLE - A nacelle for a turbojet engine is provided that includes an air intake upstream from the turbojet engine, a middle section intended to surround a fan of the turbojet engine and its case, and a downstream section. The middle section is made from at least one aerostructure capable of ensuring external aerodynamic continuity of the nacelle, and the aerostructure is rigidly bound, so as to be able to be taken apart, to at least one surrounding fixed structure. | 05-16-2013 |
20130133977 | ACOUSTIC PANEL FOR A TURBOJET ENGINE NACELLE, WITH IN-BUILT FASTENERS - An acoustic panel is provided that includes at least one cellular core arranged between at least an internal skin and an external skin, wherein the external skin incorporates at least one fastener able to collaborate in a disconnectable fashion with a complementary fastener associated with a structure to which it is to be attached. | 05-30-2013 |
20130171000 | TURBOJET ENGINE BLADE, IN PARTICULAR A GUIDE BLADE, AND TURBOJET ENGINE RECEIVING SUCH BLADES - A turbojet vane, in particular a compressor guide vane, characterized in that the vane comprises the following elements:
| 07-04-2013 |
20130213560 | METHOD FOR PRODUCING PARTS MADE FROM COMPOSITE MATERIALS WITH A BRAIDED COVERING - The invention relates to a method of making a composite material part, the method comprising the steps of:
| 08-22-2013 |
20130251519 | TURBOJET CASING AND TURBOJET RECEIVING SUCH CASINGS - A turbojet casing adapted to receive a plurality of vanes, the casing including attachment means ( | 09-26-2013 |
20130280031 | THRUST REVERSER - A thrust reverser for the nacelle of a turboreactor includes at least one fixed front frame that can be mounted downstream of a fan casing of the turboreactor and directly or indirectly supports at least one flow deviation vanes, in which at least part of the flow deviation vanes can be detached from the front frame and moved in translation independently therefrom when a maintenance operation is being carried out on the reverser. | 10-24-2013 |
20130305911 | METHOD FOR BRAIDING REINFORCING FIBRES WITH VARIATION IN THE INCLINATION OF THE BRAIDED FIBRES - The invention relates to a method of braiding reinforcing fibers on a mandrel ( | 11-21-2013 |
20130312263 | METHOD FOR MANUFACTURING AN AIR INTAKE STRUCTURE FOR A TURBOJET ENGINE NACELLE - A method for manufacturing an air-intake structure for a turbojet-engine nacelle includes two component parts, i.e. one air-intake lip structure and one outer cowl for the air-intake structure. In particular, the method includes the following steps: separately manufacturing the component parts such that each integrates one overlapping portion with a part to which is to be attached. The overlapping portion is configured such that an outer surface of the outer overlapping portion provides continuity with an outer surface of the outer cowl associated with the inner overlapping portion. To secure the overlapping portions, glue or a fastener may be used. | 11-28-2013 |
20130315657 | UNIT FOR AN AIRCRAFT THRUSTER - A unit for an aircraft thruster is provided that includes a first ferrule configured to be attached to a second ferrule and a first connection flange configured to be secured to a second corresponding connection flange secured to the second ferrule. The connection flange includes a portion forming a plane extending along a radial direction with respect to the first ferrule. A link between the first ferrule and the corresponding connection flange is offset to a distance from said plane corresponding to a length for damping a shear-generating flexural moment, generated by fluxes of forces passing through the first ferrule. | 11-28-2013 |
20140026974 | PROCESS OF MANUFACTURING A TURBOJET ENGINE NACELLE PART - A method for manufacturing a nacelle air intake lip including a plurality of components includes the following steps. The first step is positioning, inside a mold, two components within a set of fibrous layers encompassing all or part of the components so that a preform is formed. Next step is performing impregnation of the obtained preform to obtain molding of the nacelle air intake lip. | 01-30-2014 |
20140255178 | AIRCRAFT ENGINE AIR FLOW STRAIGHTENING VANE AND ASSOCIATED FLOW STRAIGHTENING STRUCTURE - A flow straightening vane made of composite materials includes a core made up of three-dimensional woven textile rods which core is surrounded by a textile covering, this core and this covering being consolidated using a thermoset resin. | 09-11-2014 |