Patent application number | Description | Published |
20120248284 | SUPPORTING STRUCTURE FOR THRUST REVERSER, IN PARTICULAR HAVING CASCADES - The present invention relates to a supporting structure ( | 10-04-2012 |
20120256051 | STUB FRAME FOR A CASCADE THRUST REVERSER STRUCTURE - The invention relates to a stub frame ( | 10-11-2012 |
20130062461 | NACELLE FOR AN AIRCRAFT ENGINE - A supporting half-structure for an aircraft engine nacelle is provided that includes at least one longitudinal beam and a front half-frame connected to each other and formed at least partly in composite materials. The half-structure includes a connecting hinge positioned in a junction area of the longitudinal beam and of the half-frame, the hinge being formed by composite materials laid out so that fibres of the composite materials are positioned in alignment with fibres of composite materials forming said front half-frame. | 03-14-2013 |
20130062462 | NACELLE FOR AN AIRCRAFT ENGINE - A supporting half-structure for an aircraft engine nacelle is provided that includes at least one longitudinal beam and a front half-frame, the beam and the half-frame being formed of composite materials. The half frame has an open section, and the half-structure defines a structure selected from the group consisting of: the beam and the front half-frame form a one-piece part; the beam has an extension with an open section, the shape of which matches that of the front half-frame, the extension being attached to the half frame; and the front half-frame has an extension with an open shape, the shape of which matches the beam, wherein the extension is attached to the beam. | 03-14-2013 |
20130161415 | BEAM FOR A CASCADE THRUST REVERSER - The present disclosure relates to a beam, in particular for a cascade thrust reverser, including a skin made of a composite material and defining a closed section, wherein said beam is filled with a core material. | 06-27-2013 |
20130230390 | LEADING EDGE STRUCTURE, IN PARTICULAR FOR AN AIR INLET OF AN AIRCRAFT ENGINE NACELLE - A leading edge structure for an air inlet of an aircraft nacelle includes a leading edge and an inner partition defining a longitudinal compartment that is located inside the leading edge and accommodates a de-icing and/or anti-icing mat. The leading edge structure includes a multi-axial composite structure placed on top of a heating element for anti-icing and/or de-icing. | 09-05-2013 |
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 |
20140252686 | METHOD FOR DETECTING THE PRESENCE OF BUBBLES DURING OPERATIONS OF INJECTING RESIN FOR THE MANUFACTURE OF FIBRE COMPOSITE COMPONENTS - A method of detecting bubbles during operations for injecting resin for the manufacture of fibre composite components, is noteworthy in that the electrical capacitance or conductivity of at least one part of the medium formed by the fibres and the liquid is measured. | 09-11-2014 |