Abstract: Leading edge of supporting surfaces of aircraft. A primary structure (EP) made without ribs is assembled with a specific frontal area (ZF) against impacts. The primary structure comprises two upper and lower covering panels (1, 2) and two diagonal and frontal spars (3, 4), which constitute the strong and rigid structural assembly of the leading edge (BA). The frontal area (ZF) is made up of one or two elemental parts which determine a kind of roof tile which closes the outer aerodynamic contour of the profile of the leading edge (BA) and provides a good behaviour against erosion, operational impacts on the ground and the impact of birds in flight. The invention is applicable to wings, stabilizers and control surfaces of aeroplanes.

Abstract: A process for manufacturing primary structures of composite material with curing in a female tool, comprising the steps of laminating superimposed composite material layers in a pre-impregnated state; placing the obtained laminate over a forming tool, loading the assembly of the laminate and forming tool in a vacuum bell and applying a pre-established forming operation, loading the formed laminate, still in a green state, in a female tool suitable for its curing, placing lateral caul plates in the tool and inserting elastomeric pipes in channels of the caul plates, fitting a central caul plate, sealing the assembly and applying a vacuum bag with perforations to remove the air from its interior. The assembly is cured in an autoclave.

Abstract: A process for manufacturing pre-cured parts of composite material with green-applied stiffeners, comprising the lamination of superimposed pre-impregnated composite material sheets to obtain a base part (1) and a second part (2) intended to be bonded with it; curing the base part (1); hot forming the laminate destined to form the second part (2); removing the second part (2) from the forming tool thereof and deposit it over the base part (1), intercalating a structural adhesive sheet between both of them; closing the assembly of both parts inside a vacuum bag and loading said bag in an autoclave, carrying out a curing cycle of the second part (2) under pressure and temperature, so that it is strongly adhered to the base part (1). The invention is applicable to the field of aeronautics.

Abstract: A process for making a dismountable and/or fixed traction-compression coupling to be applied to composite materials, in which a basic laminate (1) of composite material is folded at least once to obtain at least one skirt (2) forming an angle close to 90° with the rest of the laminate; by using a transition radius between the skirt and the rest of the laminate, a set of distribution plates (5, 6) is applied over the basic laminate to stabilize the skirt and produce a uniform load distribution, making holes in each set of distribution skirt-plates and introducing traction bolts (4) with an initial pretension in said holes, hence obtaining the connection between the components to be joined. The invention is applicable to the aerodynamic structures of aircraft.

Abstract: Leading edge of supporting surfaces of aircraft. A primary structure (EP) made without ribs is assembled with a specific frontal area (ZF) against impacts. The primary structure comprises two upper and lower covering panels (1, 2) and two diagonal and frontal spars (3, 4), which constitute the strong and rigid structural assembly of the leading edge (BA). The frontal area (ZF) is made up of one or two elemental parts which determine a kind of roof tile which closes the outer aerodynamic contour of the profile of the leading edge (BA) and provides a good behaviour against erosion, operational impacts on the ground and the impact of birds in flight. The invention is applicable to wings, stabilizers and control surfaces of aeroplanes.