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: 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: 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: A system based on integrated optical technologies for the measurement and diagnostics of physical parameters on whatever structure, by the use of optical sensors, made by the fiber embedded Bragg grating method and by the use of a planar integrated optics device for the analysis of the optical signal. The sensors may be embedded or bonded to the structure, allowing the measurement of parameters like strain and temperature, in either a static or dynamic regime. The system pertains to the technical field of the diagnostics and measurements of mechanical or thermal parameters and to the application field of ground, water and aerospace transportation and also to the application field of construction.