Abstract: A matched mold curing apparatus defining a molding cavity has two sets of layers of curable, fiber-reinforced, thermosetting composite material laminated on a lower forming tool and upper forming tool. Closed-cell foam core segments are provided and placed adjacent to each other on the layers. The core segments are oversized with respect to the nominal size determined by the molding cavity in the closed condition, minus the thickness of the layers of composite material. A controlled temperature is applied firstly to allow plastic deformation of the core segments, but without closing completely the matched mold. The temperature and pressure are then applied to cause complete closure of the matched mold and curing of the laminated layers.

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 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: 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: Method for bending pipes (T) or similar elongated elements in a pipe bending machine includes a seat for positioning the pipe (T) to be bent, a forming roller (R) having a predetermined radius (RR) around which the pipe is bent and appropriated devices for seizing and moving the pipe.

Abstract: Protection panel (3) for an aircraft suitable for being associated with at least a portion of the surface to be protected, consisting of a plurality of layers associated with each other made of aramid fibre in which at least one of said layers consists of an aramid fibre or unidirectional fabric.

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.

Abstract: Protection panel (3) for an aircraft suitable for being associated with at least a portion of the surface to be protected, consisting of a plurality of layers associated with each other made of aramid fibre in which at least one of said layers consists of an aramid fibre or unidirectional fabric.

Abstract: An acoustic board with an improved composite structure (1), suitable for reducing the sound of aircraft engines, wherein an upper layer consists of a fabric (7) having a high sensitivity to sound velocity and a supporting sheet (4) having a certain porosity; the upper layer is combined, in turn, with an intermediate honeycomb layer (2) and with a lower layer (5) of the conventional type.