Abstract: An air inlet (3) for a nacelle (2) for an aircraft (1) includes at least one acoustic panel (5), adapted to lower noise generated by the engine (21) to which the air inlet (3) is connected. At least one lip (6) defines the profile upon which an airflow flowing into the air inlet (3) acts. If necessary, at least one engine ring (4) is adapted to allow the air inlet (3) to be connected to an engine (21) of the nacelle (2). If necessary, at least one outer barrel (7) is adapted to define the outer shape of the air inlet (3) upon which an airflow acts. The air inlet (3) is manufactured as one single piece, made of a composite material.

Abstract: An air inlet (3) for a nacelle (2) for an aircraft (1) includes at least one acoustic panel (5), adapted to lower noise generated by the engine (21) to which the air inlet (3) is connected. At least one lip (6) defines the profile upon which an airflow flowing into the air inlet (3) acts. If necessary, at least one engine ring (4) is adapted to allow the air inlet (3) to be connected to an engine (21) of the nacelle (2). If necessary, at least one outer barrel (7) is adapted to define the outer shape of the air inlet (3) upon which an airflow acts. The air inlet (3) is manufactured as one single piece, made of a composite material.

Abstract: A method for making hollow stiffening elements with co-curing technique on a structure made of composite material 1 includes the use of at least a lamination and polymerization spindle 2 upon which is positioned at least a rolled section 3. The rolled section 3 forms at least a hollow structure 11 where there is the spindle 2, including the following operational phases: coating the spindle 2 with at least a first anti-adherent layer 41; coating the spindle 2 with at least a second heat-shrinking layer 42; heating the coated spindle 2; positioning the spindle 2 on the surface of the structure 1; laminating the surface 1 through at least a rolled section 3; heating the structure 1 with at least a positioned rolled section 3; extracting the spindle 2 from the hollow structure 11.

Abstract: A pin for the production and positioning of parts made of composite material and glued together in an aircraft, the pin including an elongated body (1), which is inserted in the holes purposely provided on parts of the aircraft or of the assembly jig. The pin also includes a head (2) that limits insertion of the pin in the holes, the body and the head being integrated in a single body made of a thermoplastic material. The process of production of the pin is a molding process.

Abstract: A reference tool for assembly jigs for aircraft structures includes a constraint pin (1), for being inserted into holes purposely provided on the assembly jig for aircraft structures and a reference support (2), associated with the pin, for generating a gap between the parts of the aircraft structure, during assemblage, of a known and standardized amount.

Abstract: A method for making hollow stiffening elements with co-curing technique on a structure made of composite material 1 includes the use of at least a lamination and polymerization spindle 2 upon which is positioned at least a rolled section 3. The rolled section 3 forms at least a hollow structure 11 where there is the spindle 2, including the following operational phases: coating the spindle 2 with at least a first anti-adherent layer 41; coating the spindle 2 with at least a second heat-shrinking layer 42; heating the coated spindle 2; positioning the spindle 2 on the surface of the structure 1; laminating the surface 1 through at least a rolled section 3; heating the structure 1 with at least a positioned rolled section 3; extracting the spindle 2 from the hollow structure 11.

Abstract: A pin for the production and positioning of parts made of composite material and glued together in an aircraft, the pin including an elongated body (1), which is inserted in the holes purposely provided on parts of the aircraft or of the assembly jig. The pin also includes a head (2) that limits insertion of the pin in the holes, the body and the head being integrated in a single body made of a thermoplastic material. The process of production of the pin is a molding process.

Abstract: A reference probe for assembly jigs for aircraft structures includes a constraint pin (1), for being inserted into holes purposely provided on the assembly jig for aircraft structures and a reference support (2), associated with the pin, for generating a gap between the parts of the aircraft structure, during assemblage, of a known and standardized amount.

Abstract: Process for manufacturing a sound-absorbing panel comprising the steps of lamination of a front sheet, assembly of an intermediate honeycomb sheet on the front sheet, lamination of a back sheet, polymerisation of such assembled panel and acoustic perforation of the front sheet.