Abstract: A method of realization of an aeronautical item with hybrid composite materials by means of additive technology comprising the steps of: design of the product by means of a three-dimensional mathematical model which defines, in a reference system, the shape and dimensions and includes the information associated with the areas of the item that must be reinforced according to the level of stress; deposition, by means of additive technology, of a matrix in polymeric material and of reinforcing fibers according to the mathematical model; deposition of one or more continuous fibers made of different materials along articulated paths in correspondence with the areas that must be reinforced according to the level of stress (continuous fibers oriented along paths defined by the directions of the loads or in any case in the directions provided in the design phase).

Abstract: A multifunctional composite material is provided which has a polymeric matrix filled with electrically conductive nanoparticles combined with a self-healing molecular filler selected from the group consisting of molecules and oligomers containing groups acting as donors and acceptors of hydrogen bonds.

Abstract: The method allows to monitor a composite material comprising an epoxy resin filled with electrically conductive nanoparticles, wherein at least one electrical property i.e. impedance of the composite material is influenced by being subjected to a mechanical deformation. The method provides for inserting the composite material in an electric circuit emitting an electric signal whose value depends on the electrical property, so that, when the value of the signal overcomes a given threshold value, a warning message is delivered.

Abstract: The method allows to monitor a composite material comprising an epoxy resin tilled with electrically conductive nanoparticles, wherein at least one electrical property i.e. impedance of the composite material is influenced by being subjected to a mechanical deformation. The method provides for inserting the composite material in an electric circuit emitting an electric signal whose value depends on the electrical property, so that, when the value of the signal overcomes a given threshold value, a warning message is delivered.

Abstract: A process is for preparing a self-healing composite material including a matrix of epoxy polymer in which a catalyst of ring opening metathesis reaction and vessels containing at least one monomer able to polymerize due to a ring opening metathesis reaction are dispersed. The process includes the preliminary step of dispersing at molecular level the catalyst in a mixture containing at least one precursor of the epoxy polymer, and then the steps of dispersing, in the mixture, the vessels and a tertiary amine acting as curing agent of the precursor, and the step of curing the mixture by at least a first heating stage performed at a temperature between 70 and 90° C. for a time between 1 and 5 hours, and a second heating stage performed at a temperature between 90 and 170° C. for a time between 2 and 3 hours.

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 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: An article of composite material includes a plurality of plies of material consolidated through the application of pressure and heating, in which each material ply is made by a resin matrix reinforced with fiber material. The article includes heating electrical resistance and temperature sensing devices embedded in the composite material, which are respectively placed in at least one interface zone between the material plies and are suitable to allow a temperature control of the article in service.

Abstract: The process for preparing a self-healing composite material comprising a matrix of epoxy polymer, in which a catalyst of ring opening metathesis reaction and microcapsules containing a cyclic olefin having 7 to 40 carbon atoms are dispersed, comprises the steps of: preparing a mixture of a precursor of the epoxy polymer, having at least one oxirane ring, a curing agent chosen from the group consisting of tertiary amines, a Hoveyda-Grubbs II metathesis catalyst reaction, having the formula (I), wherein Ar=aryl having at least one halogen or alkyl substituent and “R=alkyl with 1 to 20 carbon atoms, and microcapsules containing a cyclic olefin having 7 to 40 carbon atoms; and heating the mixture at a temperature comprised between 25 and 130° C. for at least 1 hour, so as to obtain such matrix of epoxy polymer due to a reaction between precursor and curing agent, which reaction does not substantially involve either said catalyst or said microcapsules.

Abstract: A process is for preparing a self-healing composite material including a matrix of epoxy polymer in which a catalyst of ring opening metathesis reaction and vessels containing at least one monomer able to polymerize due to a ring opening metathesis reaction are dispersed. The process includes the preliminary step of dispersing at molecular level the catalyst in a mixture containing at least one precursor of the epoxy polymer, and then the steps of dispersing, in the mixture, the vessels and a tertiary amine acting as curing agent of the precursor, and the step of curing the mixture by at least a first heating stage performed at a temperature between 70 and 90° C. for a time between 1 and 5 hours, and a second heating stage performed at a temperature between 90 and 170° C. for a time between 2 and 3 hours.

Abstract: The process for preparing a self-healing composite material comprising a matrix of epoxy polymer, in which a catalyst of ring opening metathesis reaction and microcapsules containing a cyclic olefin having 7 to 40 carbon atoms are dispersed, comprises the steps of: preparing a mixture of a precursor of the epoxy polymer, having at least one oxirane ring, a curing agent chosen from the group consisting of tertiary amines, a Hoveyda-Grubbs II metathesis catalyst reaction, having the formula (I), wherein Ar=aryl having at least one halogen or alkyl substituent and “R=alkyl with 1 to 20 carbon atoms, and microcapsules containing a cyclic olefin having 7 to 40 carbon atoms; and heating the mixture at a temperature comprised between 25 and 130° C. for at least 1 hour, so as to obtain such matrix of epoxy polymer due to a reaction between precursor and curing agent, which reaction does not substantially involve either said catalyst or said microcapsules.

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: An article of composite material includes a plurality of plies of material consolidated through the application of pressure and heating, in which each material ply is made by a resin matrix reinforced with fiber material. The article includes heating electrical resistance and temperature sensing devices embedded in the composite material, which are respectively placed in at least one interface zone between the material plies and are suitable to allow a temperature control of the article in service.

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: A leading edge structure is described for wing structures and empennage, comprising an outer shell suitable to define a front portion of a airfoil. The outer shell is formed by a bent plate of fiber-reinforced thermoplastic resin composite material. The structure further comprises an inner shell having a convex profile that is oriented in the same direction as the profile of outer shell, which is formed by a bent plate of fiber-reinforced thermoplastic resin composite material and is bonded to the outer shell at the longitudinal edges thereof, and at least one reinforcing element, transversally extending such as to connect the outer shell and inner shell to each other , which is formed by at least one piece of fiber-reinforced resin composite material and is fixed at opposite ends to the outer shell and inner shell, respectively.