Abstract: Gripping claws and pairs of arched angular profiles are arranged along the perimeter of a cylindrical surface segment so as to grip the edges of a fuselage panel, closing the opening of a pressurizable chamber.

Abstract: In order to manufacture beams of composite material with a J-shaped cross-section, a curing apparatus includes a bar supported parallel to a table by two end supports. A J-shaped beam of uncured composite material is prepared and arranged on the apparatus, positioning the bottom flange of the beam so that it faces the table and resting the web and the upper flange against two respective sides of the bar. The beam is covered with a vacuum bag and pressure and heat are applied inside an autoclave in order to cure the resin in the beam.

Abstract: A jet of air is impelled on to the upper surface of a flap in order to increase its lift. Part of the air in this air jet is drawn, through air intakes, from the air stream flowing over an upper surface of the fixed part of the wing, located upstream of the flap. The air jet drawn in by suction by the air intakes is reinforced by a jet of compressed air blown through a passage which opens immediately downstream of the air intakes. This creates a combined jet of the air sucked in and the blown jet, which is ejected on to the upper surface of the flap through outlet apertures located on the rear edge of the fixed part of the wing.

Abstract: A method for estimating an angle of attack and an angle of sideslip of an aircraft has a plurality of control surfaces each adjustable with respect to an associated reference surface. The method includes measuring quantities representative of the angle formed by each control surface with respect to the associated reference surface; measuring the effective rolling speed, the effective pitching speed, and effective yawing speed of the aircraft. A linearized model of a state observer is defined according to the following equations: { ? x .

Abstract: The invention concerns a plant for manufacturing parts made of composite material, in particular sections for an aircraft fuselage, having at least a compaction station in which, in operation, there are provided a mandrel coated of composite material to be compacted and a transport mechanism arranged to transport at least one compaction device on said composite material. The transport mechanism is associated with at least one sling having at least one strip of porous material that, in operation, is in direct contact with the compaction device, and the sling is configured to transport the compaction device onto the composite material through application of a vacuum source at least to the strip of porous material. The invention also concerns a method of and an apparatus for manufacturing parts made of composite material.

Abstract: A pre-impregnated material includes a resin matrix reinforced with a fiber material. The matrix has a semi-crystalline layer based on semi-crystalline thermoplastic resin having a melting point Tf, on at least one side of which there is an amorphous surface layer based on amorphous thermoplastic resin having a glass transition temperature Tg, in which the glass transition temperature Tg of the amorphous thermoplastic resin is below the melting point Tf of the semi-crystalline thermoplastic resin.

Abstract: A leading edge structure includes two or more multilayer panels at least partially overlapping and suitably curved with at least partially congruent concavities. Each multilayer panel includes at least the following three layers: a first metal foil layer metal foil, a second intermediate layer of fibre-glass securely fixed to the first layer, and a third metal honeycomb layer securely fixed to the second layer.

Abstract: A method of manufacturing a Z-section component from composite material uses a mould having a convex mould portion and a concave mould portion. The method includes the preparation of a vacuum bag for a polymerization cycle, including the covering the fresh component with a layer of peel ply formed from a plurality of strips of peel ply and fixing the layer of peel ply perimetrically to the mould using an adhesive tape. A line of sealant is positioned perimetrically above the adhesive tape around the fresh component and a separator film is positioned above the layer of peel ply so as to cover the layer of peel ply and the perimetric line of sealant. A ventilation textile is placed perimetrically on the mould, the textile having an aperture which is positioned so as to leave uncovered an underlying part substantially coinciding with the fresh component. A vacuum bag is applied for the polymerization cycle.

Abstract: The process for monitoring the curing reaction of a polymeric matrix, in which carbon nanotubes are dispersed whereby a composite material is formed, provides for: arranging an electric circuit comprising at least a generator of a substantially constant voltage, an amperemeter and two electrodes immersed into the composite material, whereby the composite material interposed between the electrodes closes the electrical circuit, and tracing the current intensity value measured by the amperemeter, which is correlated to the progress of the curing reaction of the polymeric matrix, so as to control said progress.

Abstract: A covering structural element is adapted to close an elongate gap provided on an aerodynamic surface of an aircraft. Such an element has a strip-shaped body made of metal material, including a fixing portion, adapted to be fixed along one of the longitudinal borders of the elongate gap; a sliding portion adapted to urge in a sliding manner on the other of the longitudinal borders of the strip-shaped gap; and a connection portion, connecting the sliding portion to the fixing portion, the thickness of which is so sized as to allow, in use, a controlled elastic bending of the structural covering element. The covering structural element has a profile so sized as to be tapered at the transition from the fixing portion to the connection portion and from the sliding portion to the connection portion, the covering structural element having a smooth surface on the side intended to face away from the elongate gap.

Abstract: A system and a method are for the estimation of the impact area of a smart load that can be launched from an aircraft as a function of data or signals indicative of the aircraft flight conditions upon release of the load and of predetermined impact conditions on the target. The estimation of a polygonal impact area defined by the coordinates of a central point and of a predetermined number of vertices is by corresponding neural networks.

Abstract: A wing-flap assembly includes a flap made up of a plurality of flap sections, in which each flap section is connected to the preceding one in a rotatable manner, and one or more actuator devices adapted to control the rotation of the flap sections. Each actuator device includes an extended element made of shape memory alloy and an arch-shaped framework made of elastic material, to which the extended element is fixedly connected under tension. Each end of the extended element is fixed to a respective end of the arch-shaped framework. At least one of the actuator devices is connected at one end to the first of the flap sections, and on the other side it is adapted to be connected to a wing structure.

Abstract: The present invention relates to a system to manufacture composite material parts comprising a supporting mandrel having at least one compacting zone configured to contain at least one composite material element to be compacted by applying a certain degree of vacuum. The system comprises also at least one compacting equipment comprising a frame having a plurality of interconnected arms along a predetermined perimeter, at least one vacuum bag attached to a side of the frame along its perimeter and configured to compact the element, at least one porous material attached to the vacuum bag along the frame's perimeter and configured to adhere in a removable way to the compacting zone and to impede the air influx during the compacting of element. The invention also relates to a compacting equipment and to a method to manufacture composite material parts.

Abstract: For the manufacture of a dry preform intended for reinforcing a composite structural member of an aircraft, a digitally controlled automatic machine similar to an embroidery machine deposits and stitches successive layers of continuous reinforcing fibres. In each layer the fibres are oriented and distributed according to a predetermined scheme. A preform is obtained having a predetermined three-dimensional shape in which the reinforcing fibres are distributed and oriented an in optimum manner.

Abstract: Multi-layer composite product, featuring low emissivity in the mid-infrared band (as wavelength range 2,5–5 ?m) and far-infrared (as wavelength range 8.0–14.0 ?m) bands, as well as low reflexivity in the near-infrared (at a wavelength range of 0.7–2.5 ?m) and in the visible (as wavelength range 0.3–0.7 ?m) bands, including a base constructed with low-density and/or high thermal-resilience structural materials, covered with optionally doped coating, and where, between the base and the coating, at least one intermediate layer of metals or metal oxides is planned for insertion.

Abstract: A method of manufacturing a stringer for a fuselage skin panel comprises the steps of:

Abstract: The process for anodizing a workpiece of aluminum or aluminum alloys provides for the use of the workpiece as the anode of an electrolytic cell in the presence of an aqueous acid solution which contains from 10 to 200 g sulfuric acid and from 5 to 200 g L(+)-tartaric acid.