Abstract: An impression chamber (1) for a 3D printer (6) adapted to receive a high performance plastic filament (19) and including a print head (7) and a printing bed (8), wherein the impression chamber (1) includes a thermally insulated plate (2) and a polyimide film (3) attached to the plate (2) for delimiting a printing space (20). The plate (2) is dimensioned to have a surface (2a) equal or larger than the major surface of the piece (5) to be printed, and the film (3) is dimensioned to surround the printing bed (8). The plate (2) is provided with a first through-hole (15) for allowing the passage of at least part of the print head (7), so that the plate (2) is moved by the movement of the print head (7) and the film (3) is dragged by said movement providing a flexible impression chamber (1).

Abstract: A method for manufacturing a stiffened panel made from composite material comprising a skin and elongated reinforcing elements wherein some of the elongated reinforcing elements cross each other. The method comprises the steps of (a) laying up a flat laminate comprising stacked plies of composite layers for forming a structure comprising the elongated reinforcing elements of the panel, (b) cutting the flat laminate along intersection lines of planes defining the webs of two crossing reinforcing elements, (c) cutting in the flat laminate the outline of the elongated reinforcing elements, (d) forming the structure comprising the elongated reinforcing elements of the panel, (e) laying up plies of composite layers for forming the skin, and (f) curing the laid-up plies of the skin and the formed structure comprising the elongated reinforcing elements.

Abstract: An impression chamber (1) for a 3D printer (6) adapted to receive a high performance plastic filament (19) and including a print head (7) and a printing bed (8), wherein the impression chamber (1) includes a thermally insulated plate (2) and a polyimide film (3) attached to the plate (2) for delimiting a printing space (20). The plate (2) is dimensioned to have a surface (2a) equal or larger than the major surface of the piece (5) to be printed, and the film (3) is dimensioned to surround the printing bed (8). The plate (2) is provided with a first through-hole (15) for allowing the passage of at least part of the print head (7), so that the plate (2) is moved by the movement of the print head (7) and the film (3) is dragged by said movement providing a flexible impression chamber (1).

Abstract: A method for manufacturing a stiffened panel made from composite material comprising a skin and elongated reinforcing elements wherein some of the elongated reinforcing elements cross each other. The method comprises the steps of (a) laying up a flat laminate comprising stacked plies of composite layers for forming a structure comprising the elongated reinforcing elements of the panel, (b) cutting the flat laminate along intersection lines of planes defining the webs of two crossing reinforcing elements, (c) cutting in the flat laminate the outline of the elongated reinforcing elements, (d) forming the structure comprising the elongated reinforcing elements of the panel, (e) laying up plies of composite layers for forming the skin, and (f) curing the laid-up plies of the skin and the formed structure comprising the elongated reinforcing elements.

Abstract: Non-straight ducts for conducting fluids at temperatures higher than 280° C. and pressures higher than 4 bar made of a composite material and, particularly, hot air bleed ducts of an aircraft made of a carbon-fiber reinforced polymer aimed to reduce weight of the bleeding system by replacing most of the metallic material from which the bleeding ducts are currently made.

Abstract: The invention relates to an aircraft with a protection shield for the rear composite material, fuselage 25) for conducting tail impact tests, in addition to a tail absorber, the shield (11) being formed by a plurality of pieces (21) joined to supports (23) fixed to the rear fuselage (25) behind the tail absorber (1), said pieces (21) having a laminar structure with an outer steel sheet (13), an inner composite sheet (17) and an intermediate high resistance silicon sheet (15).

Abstract: The invention relates to an aircraft with a protection shield for the rear composite material, fuselage 25) for conducting tail impact tests, in addition to a tail absorber, the shield (11) being formed by a plurality of pieces (21) joined to supports (23) fixed to the rear fuselage (25) behind the tail absorber (1), said pieces (21) having a laminar structure with an outer steel sheet (13), an inner composite sheet (17) and an intermediate high resistance silicon sheet (15).