Abstract: Protection of elements (1) of composite material protected at its points of complex geometry, such as various edges and corners, against electric discharges to which they are potentially exposed, said elements (1) being obtained by applying a cycle of temperature and pressure to a composite material arranged in a mold (2) designed in such a way that, once the geometry of the element (1) is known, the mold (2) includes free spaces (6) intended for the accumulation of resin from the process of manufacture of said element (1), and said resin will form the dielectric protection of the various edges or corners of the element (1) as it builds up, forming layers (3) that are disposed around the free edges of the element (1), thus endowing these surfaces of various edges or corners with dielectric protection of electrical insulation that prevents possible discharges and expulsion of hot particles in the case of electric discharge on said element (1).

Abstract: A device (1) for the installation of a conducting component (2) on a structure (3) made from composite material, the inside of this structure (3) comprising a substance which can be ignited, which comprises an installation element (4) onto which the conducting component (2) is positioned, a conducting insert element (5), by means of which the installation element (4) is joined to the composite material structure (3) by its internal part, a conducting layer (6) arranged on the external part of the installation element (4) and a conducting fixing element (7) which joins the structure (3) and the installation element (4) to the insert element (5) and the conducting layer (6) so that the device (1) defines a low impedance current path through the conducting layer (6) and the insert element (5) through which the energy is dissipated from an atmospheric discharge to the component (2) or to the structure (3), the interior face of the structure (3) remaining isolated.

Abstract: Lightning strike protection in aircraft: the invention refers to a lightning strike protection system for fuel tank access covers (10) in composite structures having a skin (30), this system comprising an outer cover (12) made of metallic material, that coats externally the fuel tank access covers (10) and an inner cover (13) made of composite material, the outer cover (12) also comprising a lip element (14), made of the same metallic material than that of the outer cover (12) and being integrated in its structure, and a conductive visco-elastic material or spring element (15) provided over the mentioned lip element (14).

Abstract: This invention relates to a protection device against electrical discharges to an aircraft, especially against lightning, applicable to an external structural surface element (1), completely or partially built from a composite, comprising at least one metallic attachment element (7) with countersinking, a fine metallic mesh (2) for outer protection of said surface (1), a thick metallic mesh (5) in an area around the attachment elements (7); a metallic part (11) fixed to the inner face of the surfacing (1) by means of an attachment element (7); and a metallic washer (9) surrounding the countersunk area of the to attachment element (7) with which said metallic meshes (2, 5) come into contact.

Abstract: A device (1) for the installation of a conducting component (2) on a structure (3) made from composite material, the inside of this structure (3) comprising a substance which can be ignited, which comprises an installation element (4) onto which the conducting component (2) is positioned, a conducting insert element (5), by means of which the installation element (4) is joined to the composite material structure (3) by its internal part, a conducting layer (6) arranged on the external part of the installation element (4) and a conducting fixing element (7) which joins the structure (3) and the installation element (4) to the insert element (5) and the conducting layer (6) so that the device (1) defines a low impedance current path through the conducting layer (6) and the insert element (5) through which the energy is dissipated from an atmospheric discharge to the component (2) or to the structure (3), the interior face of the structure (3) remaining isolated.

Abstract: This invention relates to a protection device against electrical discharges to an aircraft, especially against lightning, applicable to an external structural surface element (1), completely or partially built from a composite, comprising at least one metallic attachment element (7) with countersinking, a fine metallic mesh (2) for outer protection of said surface (1), a thick metallic mesh (5) in an area around the attachment elements (7); a metallic part (11) fixed to the inner face of the surfacing (1) by means of an attachment element (7); and a metallic washer (9) surrounding the countersunk area of the attachment element (7) with which said metallic meshes (2, 5) come into contact.

Abstract: Protection of elements (1) of composite material protected at its points of complex geometry, such as various edges and corners, against electric discharges to which they are potentially exposed, said elements (1) being obtained by applying a cycle of temperature and pressure to a composite material arranged in a mould (2) designed in such a way that, once the geometry of the element (1) is known, the mould (2) includes free spaces (6) intended for the accumulation of resin from the process of manufacture of said element (1), and said resin will form the dielectric protection of the various edges or corners of the element (1) as it builds up, forming layers (3) that are disposed around the free edges of the element (1), thus endowing these surfaces of various edges or corners with dielectric protection of electrical insulation that prevents possible discharges and expulsion of hot particles in the case of electric discharge on said element (1).

Abstract: The present invention relates to a method for evaluating the effect of an electric discharge on an aircraft structure through the evaluation of the damage caused by the effect of the thermal heating generated by the mentioned discharge on the structure, including the steps of: applying an electric discharge on the material of the aircraft structure using an intensity generator; distributing in an electric mesh with resistive electric elements the material of the aircraft structure; calculating the intensities running through the electric mesh of the material of the aircraft structure from the intensity introduced in the generators; calculating with the previous intensities the heat which is dissipated in each of the elements of the electric mesh of the material of the aircraft structure; calculating the distribution of temperatures in each of the elements of the electric mesh of the material of the aircraft structure; determining the elements of the electric mesh of the material of the aircraft structure whic

Abstract: The present invention relates to a method for evaluating the effect of an electric discharge on an aircraft structure through the evaluation of the damage caused by the effect of the thermal heating generated by the mentioned discharge on the structure, comprising the steps of: applying an electric discharge on the material of the aircraft structure by means of an intensity generator; distributing in an electric mesh with resistive electric elements the material of the aircraft structure; calculating the intensities running through the electric mesh of the material of the aircraft structure from the intensity introduced in the generators; calculating with the previous intensities the heat which is dissipated in each of the elements of the electric mesh of the material of the aircraft structure; calculating the distribution of temperatures in each of the elements of the electric mesh of the material of the aircraft structure; determining the elements of the electric mesh of the material of the aircraft structu

Abstract: Lightning strike protection system for aircraft fuel tanks made of low electrical conductivity composite material. The system comprises an electrical conductive thin wire mesh (1) that covers the whole external surface of the tank outer skin (I) made of composite and a thick wire metallic mesh (2) overlapping the mesh (1) at a minimum distance of 50 mm to both sides of a row of fasteners (III) joining the said outer skin (I) to one internal part (II) of either composite or metallic material. Both metallic meshes (1, 2) maintain electrical contact by their installation/assembly and by means of metallic countersunk head washers (3) connected to bonding points and set to the gap existing between the fastener (III) and the outer skin (I). The corresponding fabrication process is also described.

Abstract: Lightning strike protection system for aircraft fuel tanks made of low electrical conductivity composite material. The system comprises an electrical conductive thin wire mesh (1) that covers the whole external surface of the tank outer skin (I) made of composite and a thick wire metallic mesh (2) overlapping the mesh (1) at a minimum distance of 50 mm to both sides of a row of fasteners (III) joining the said outer skin (I) to one internal part (II) of either composite or metallic material. Both metallic meshes (1, 2) maintain electrical contact by their installation/assembly and by means of metallic countersunk head washers (3) connected to bonding points and set to the gap existing between the fastener (III) and the outer skin (I). The corresponding fabrication process is also described.