Abstract: A method of manufacturing a wing structure includes laying a plurality of layers of preimpregnated material on a first mould half and on a second mold half so as to form a first fresh skin and a second fresh skin of the wing structure. A plurality of layers of preimpregnated material are laid in succession on a shaped apparatus to form a fresh leading edge skin of the wing structure. Fresh spars of preimpregnated material are formed. A wedgelike body of expanded plastics material is formed, this body being designed to be interposed between the first and second skins at the trailing edge of the wing structure. The fresh spars are positioned in a coordinated way on the first fresh skin, removable support members also positioned next to the spars. The second mold half is turned over on to the first mold half so as to position the second fresh skin on the spars and the supports, to produce a fresh wing structure. The fresh wing structure is subjected to a polymerization cycle, using a vacuum bag.

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: 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 method of manufacturing a wing structure includes laying a plurality of layers of preimpregnated material on a first mould half and on a second mold half so as to form a first fresh skin and a second fresh skin of the wing structure. A plurality of layers of preimpregnated material are laid in succession on a shaped apparatus to form a fresh leading edge skin of the wing structure. Fresh spars of preimpregnated material are formed. A wedgelike body of expanded plastics material is formed, this body being designed to be interposed between the first and second skins at the trailing edge of the wing structure. The fresh spars are positioned in a coordinated way on the first fresh skin, removable support members also positioned next to the spars. The second mold half is turned over on to the first mold half so as to position the second fresh skin on the spars and the supports, to produce a fresh wing structure. The fresh wing structure is subjected to a polymerization cycle, using a vacuum bag.

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: 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: Austenitic steel with improved high-temperature strength and corrosion resistance, characterized by the simultaneous presence, in defined quantities, of Nb, Mo and V and by the presence of C and N in a specific ratio with said three elements.

Abstract: A process for heat treatment of austenitic and ferritic stainless steel wire rod, comprising rolling a stainless steel wire rod with a finishing-rolling temperature (FRT) between 850.degree. C. and 1050.degree. C. The rod is then held at a temperature between FRT -50.degree. C. and FRT +100.degree. C. for 15 to 30 minutes, and is then wire cooled. For the manufacture of austenitic stainless steel wires for the manufacture of springs, the finishing rolling temperature is 1000.degree.-1050.degree. C., followed immediately by water cooling.

Abstract: Austenitic steel with improved high-temperature strength and corrosion resistance, characterized by the simultaneous presence, in defined quantities, of Nb, Mo and V and by the presence of C and N in a specific ratio with said three elements.