Abstract: A method is described for manufacturing a structural element in composite material extending along a straight or curvilinear longitudinal direction, having a Z-shaped cross section and comprising, in its final configuration, a central web and two flanges extending at a given final angle from opposite end portions of the web in respective directions opposite to one another; the method including the steps of: arranging a plurality of layers of composite material on a shaped portion of a forming mold; laminating the layers on the shaped portion so that the web is arranged, at least partially, in its final configuration, that a first flange is arranged in its final configuration at the final angle with respect to the portion of the web arranged in its final configuration, and that a second flange is arranged in its initial configuration at an initial angle distinct from, and greater than, said final angle with respect to the portion of the web arranged in its final configuration; moving a movable portion of the f

Abstract: The invention relates to a monolithic structure in composite material manufactured starting from a fiber-reinforced prepreg material and comprises two walls facing each other and at least one interconnection element extending transversely between the walls, connected to them and delimiting with the latter respective elongated cavities; wherein the walls extend symmetrically at opposite sides of a direction; the interconnection element is a rib extending transversely to the aforesaid direction; at least one wall has a sandwich configuration and comprises two panels facing each other and at least one spar member, which extends transversely between the panels, is connected to them, delimits with the latter respective elongated cavities and extends transversally to the rib.

Abstract: A compression molding device configured for the production of a part in composite material starting from a plate in composite with a thermoplastic matrix is described. The device comprises: a fixed support structure; an upper half-die provided with a first contoured surface corresponding to the profile of an upper surface of the part to be made; a lower half-die provided with a second contoured surface corresponding to the profile of a lower surface of the part to be made; holding means carried by the support structure and configured to hold the plate in a position interposed between the half-dies; and moving means for moving at least one of the half-dies from and towards the plate. The holding means comprise two or more releasable grippers gripping by friction distinct portions of the peripheral edge of the plate and configured to completely release or allow the complete release of the plate.

Abstract: A process for manufacturing a structural component made of composite material comprising a skin and at least one stiffening stringer applied rigidly and integrally to one face of the skin. The process comprises a) arranging, on a tool, a plurality of first layers of uncured or pre-cured composite material, forming the stringer and having a raised portion protruding from at least one flange; b) arranging, on the tool, a plurality of second layers of uncured or pre-cured composite material forming the skin; c) making a face of the skin and the flange of the stringer adhere to each other; d) applying a predetermined temperature and pressure on the assembly to compact the layers together, possibly curing the uncured material and rigidly joining the skin to the stringer; and e) performing a cutting operation on the free end side edge/s of the flange in a slanted direction.

Abstract: A process for manufacturing a structural component made of composite material comprising a skin and at least one stiffening stringer applied rigidly and integrally to one face of the skin. The process comprises a) arranging, on a tool, a plurality of first layers of uncured or pre-cured composite material, forming the stringer and having a raised portion protruding from at least one flange; b) arranging, on said tool, a plurality of second layers of uncured or pre-cured composite material forming said skin; c) making a face of said skin and flange adhere to each other; d) applying predetermined temperature and pressure on the assembly, possibly curing the uncured material and rigidly joining said skin to said stringer; e) performing a cutting operation on the free end side edge/s of said flange; and f) cover said end side edge/s of the end of said flange with a coating of composite material.

Abstract: A portable welding device comprising: a base facing a work surface, designed to receive tapes in electrically conductive composite materials to be joined or defined by at least one already positioned tape; an operating head receiving one tape at a time and movable with respect to the base along at least a first movement line parallel to the work surface; a motorized arm connecting the operating head to the base and selectively activatable to impart movements to the operating head; and feeding means selectively activatable to feed one tape at a time to the operating head and connected to the operating head; the operating head comprises a positioning roller receiving a tape at a time; a pressure roller spaced from and aligned with the positioning roller along the first movement line; and an inductor interposed between the positioning roller and the pressure roller with reference to the first movement line.

Abstract: The invention relates to a method for manufacturing a composite aircraft window frame; the method comprises the steps of: a) positioning in a mold a preform made of pre-impregnated material including dispersed fibers, with a predefined orientation, in a thermosetting resin matrix; b) closing the mold so as to define a gap between at least one surface of said preform and a portion of said mold; c) injecting thermosetting resin into the closed mold through an inlet opening of the mold itself, so as to fill the gap and completely lap said surface of the preform; and d) applying a uniform hydrostatic pressure on the surface by the injection of the resin.

Abstract: A composite material, in particular for aeronautical applications, comprising: a first pre-impregnated layer having a resin-based matrix reinforced with fibres to give the first layer predefined mechanical properties; and a second layer of magnetic field intensifier material, superimposed on a face of the first layer and joined to the first layer along that face; the second layer comprises electrically conductive fibres, preferably of carbon, dispersed in the second layer in at least two directions with different orientations and having equivalent electrical resistivity, parallel to the aforementioned face, of less than 600 ??m, preferably less than 200 ??m and even more preferably less than 100 ??m, so as to facilitate localized heating by electromagnetic induction; the first and second layers joined together define a lamina of super-weldable composite material.

Abstract: An electronic tool monitoring system to monitor usage and wear of tools for mechanical machining, comprising, for each tool to be monitored, a tag with a unique identifier and a self-contained, stand-alone electronic monitoring device. The electronic monitoring device comprises: an electronic sensory arrangement; an electronic communication interface; an electronic operator; and an electronic control unit. The electronic communication interface and the electronic operator interface are programmed to store data indicative of a service life of the tool, identify and monitor usage and wear of the tool based on an output of the electronic sensory arrangement, and estimate residual service life of the tool based on monitored usage and wear of the tool and the stored data indicative of service life of the tool. The system will implement certain actions based on whether the service life of the tool is determined to be exhausted.

Abstract: The invention relates to a method for manufacturing a box-shaped monolithic structure with a cavity by curing a fiber-reinforced prepreg material. The method comprises using two or more elongated and internally hollow support tools which have a complementary form to that of the cavities to be manufactured, and a composition based on reinforcement material and polymer suitable to allow the passage from a rigid state to a flexible elastomeric state and vice versa in response to heating/cooling down. In the rigid state, the support tools allow the direct lamination of the prepreg material on their external walls and are configured to set the flexible elastomeric state at a temperature lower than the curing temperature and higher than 50° C. During the curing operation, the curing pressure is applied both outside the structure being formed and inside the support tools, whose walls have become flexible, to push on the prepreg material to be cured.

Abstract: The invention relates to a method for manufacturing a composite aircraft window frame; the method comprises the steps of: a) positioning in a mold a preform made of pre-impregnated material including dispersed fibers, with a predefined orientation, in a thermosetting resin matrix; b) closing the mold so as to define a gap between at least one surface of said preform and a portion of said mold; c) injecting thermosetting resin into the closed mold through an inlet opening of the mold itself, so as to fill the gap and completely lap said surface of the preform; and d) applying a uniform hydrostatic pressure on the surface by the injection of the resin.

Abstract: A compression molding device configured for the production of a part in composite material starting from a plate in composite with a thermoplastic matrix is described. The device comprises: a fixed support structure; an upper half-die provided with a first contoured surface corresponding to the profile of an upper surface of the part to be made; a lower half-die provided with a second contoured surface corresponding to the profile of a lower surface of the part to be made; holding means carried by the support structure and configured to hold the plate in a position interposed between the half-dies; and moving means for moving at least one of the half-dies from and towards the plate. The holding means comprise two or more releasable grippers gripping by friction distinct portions of the peripheral edge of the plate and configured to completely release or allow the complete release of the plate.

Abstract: A portable welding device comprising: a base facing a work surface, designed to receive tapes in electrically conductive composite materials to be joined or defined by at least one already positioned tape; an operating head receiving one tape at a time and movable with respect to the base along at least a first movement line parallel to the work surface; a motorized arm connecting the operating head to the base and selectively activatable to impart movements to the operating head; and feeding means selectively activatable to feed one tape at a time to the operating head and connected to the operating head; the operating head comprises a positioning roller receiving a tape at a time; a pressure roller spaced from and aligned with the positioning roller along the first movement line; and an inductor interposed between the positioning roller and the pressure roller with reference to the first movement line.

Abstract: A method determines the tack of a material placed in contact with a surface. A sample is provided of the material, the sample including a sheet whose width increases from a first narrow end to a second wide end. The sample is applied to an upwards facing supporting surface of plate. The sample is compacted against the supporting surface of plate and a weight is attached to the first end of the sample. The plate is turned over in such a way that the supporting surface faces downwards. The detachment of the sample from the supporting surface is measured in terms of distance detached from the first end of the sample as a function of time.

Abstract: A method determines the tack of a material placed in contact with a surface. A sample is provided of the material, the sample including a sheet whose width increases from a first narrow end to a second wide end. The sample is applied to an upwards facing supporting surface of plate. The sample is compacted against the supporting surface of plate and a weight is attached to the first end of the sample. The plate is turned over in such a way that the supporting surface faces downwards. The detachment of the sample from the supporting surface is measured in terms of distance detached from the first end of the sample as a function of time.