Abstract: A method of assembling an aircraft radome and a radome comprising at least a first skin and a second skin arranged on two opposite faces of the same shell, the first skin and the second skin being formed from a first assembly of skin pieces and from a second assembly of skin pieces, respectively, the assemblies being such that all or some of the skin pieces of the first and second assemblies partially overlap one or more neighboring skin pieces of the assembly that includes them, and such that the ratio between the surface area of a piece of skin overlapping one or more neighboring pieces of skin and the total surface area of that piece of skin does not exceed a predetermined threshold value.

Abstract: A device measures a flight parameter of an aircraft which has a radome. Systems measure the deformation of a wall of the radome due to forces exerted by the air on the radome. A computer computes the flight parameter from deformation measurements obtained by the systems. The systems have an optical fiber carried by the radome provided with Bragg gratings. Each fiber has a plurality of Bragg gratings distributed over a length of the fiber so as to distribute the Bragg gratings over the radome when the fiber is installed.

Abstract: A lightning diverter system configured to equip a radome of an aircraft comprises a segmented strip configured to transmit lightning by ionization of the air to a point of junction with the aircraft structure. The segmented strip is configured to be installed on an inner wall of the radome. The lightning diverter system comprises at least one metal block configured to be installed in a through-hole of the radome, so as to be flush with an outer wall of the radome opposite to the inner wall and which is configured to be subject to an airflow when the aircraft is moving. The arrangement of the segmented strip and of the metal block or blocks is such that, when the lightning strikes the metal block on the outer wall of the radome, the lightning is transmitted to the segmented strip on the inner wall of the radome.

Abstract: A system for emitting and/or receiving electromagnetic waves embedded in an aircraft, the aircraft including an emitting and/or receiving device for emitting and/or receiving electrical signals, a radome having an electrically insulating protective envelope (12), on which at least one lightning arrester strip (21) is arranged, the radome being attached to a metal frame of the aircraft (30), a first part of the at least one lightning arrester strip is electrically connected to the metal frame of the aircraft, a second part of the at least one lightning arrester strip is connected to the emitting and/or receiving device via a metal element (35) of a predetermined shape, the at least one lightning arrester strip forming an antenna and a part of the metal element (35) is placed at a predetermined distance (d) from a part of the metal frame of the aircraft (30) for forming a capacitive link between the metal element and the metal frame of the aircraft.

Abstract: A device for measuring at least one flight parameter such as the airspeed, the sideslip angle or the angle of attack, or any other parameter dependent thereon, of an aircraft including a radome, including systems for measuring the deformation of the radome wall due to forces exerted by the air on the radome and a computer for computing from deformation measurements obtained by the systems the required flight parameter or parameters. The systems include at least one optical fiber carried by the radome provided with Bragg gratings, each fiber including a plurality of Bragg gratings distributed over a length of the fiber so as to distribute the Bragg gratings over the radome when the fiber is installed.

Abstract: A system for emitting and/or receiving electromagnetic waves embedded in an aircraft, the aircraft including an emitting and/or receiving device for emitting and/or receiving electrical signals, a radome having an electrically insulating protective envelope (12), on which at least one lightning arrester strip (21) is arranged, the radome being attached to a metal frame of the aircraft (30), a first part of the at least one lightning arrester strip is electrically connected to the metal frame of the aircraft, a second part of the at least one lightning arrester strip is connected to the emitting and/or receiving device via a metal element (35) of a predetermined shape, the at least one lightning arrester strip forming an antenna and a part of the metal element (35) is placed at a predetermined distance (d) from a part of the metal frame of the aircraft (30) for forming a capacitive link between the metal element and the metal frame of the aircraft.

Abstract: A lightning protection system for a radome, the system comprising at least one lightning protection strip positioned on an inner wall of the radome, wherein the lightning protection strip defines, on the inner wall of the radome, a curve that is substantially perpendicular, at all points thereof, to the polarization direction of the electrical field vector radiated by an antenna across from the inner wall of the radome.

Abstract: A method for opening a dome for the protection of a device to be protected, fitted in a part described as fixed, in which, in the initial position before opening, a generally plane interface separates the dome from the fixed part, is provided. The method includes connecting the dome to the fixed part by at least two independent double-link connections that are movable in rotation between the dome and the fixed part. The links in a single connection being fitted in common to the dome and to the fixed part to form overall a pantograph in the shape of an isosceles trapezium which, during opening, opens out by pivoting until maximum opening is achieved, so that the dome moves away from the fixed part via a combination of movements in translation and in rotation.

Abstract: A method for opening a dome for the protection of a device to be protected, fitted in a part described as fixed, in which, in the initial position before opening, a generally plane interface separates the dome from the fixed part, is provided. The method includes connecting the dome to the fixed part by at least two independent double-link connections that are movable in rotation between the dome and the fixed part. The links in a single connection being fitted in common to the dome and to the fixed part to form overall a pantograph in the shape of an isosceles trapezium which, during opening, opens out by pivoting until maximum opening is achieved, so that the dome moves away from the fixed part via a combination of movements in translation and in rotation.

Abstract: A lightning conductor system for a support structure having an external face intended to be subjected to a flow of air and an internal face opposite the external face, the lightning conductor system comprising an electrically conducting lightning conductor strip, intended to be placed on the side of the internal face of the support structure while being connected to ground, and means of fixing the lightning conductor strip to the support structure, the fixing means comprising fixing studs intended to be inserted into orifices formed in the support structure, said fixing studs being in electrical contact with the lightning conductor strip. The lightning conductor system includes the lightning conductor strip being mounted in an offset manner with respect to the main axes of the fixing studs.

Abstract: An aircraft latch including a main hook; an operating lever; a safety device; a button on the operating lever and fastened to the safety device; and adjustment means attached to the safety device for adjusting the position of the safety device with respect to the main hook.

Abstract: A lightning conductor system for a support structure having an external face intended to be subjected to a flow of air and an internal face opposite the external face, the lightning conductor system comprising an electrically conducting lightning conductor strip, intended to be placed on the side of the internal face of the support structure while being connected to ground, and means of fixing the lightning conductor strip to the support structure, the fixing means comprising fixing studs intended to be inserted into orifices formed in the support structure, said fixing studs being in electrical contact with the lightning conductor strip. The lightning conductor system includes the lightning conductor strip being mounted in an offset manner with respect to the main axes of the fixing studs.

Abstract: A lightning protection system for a radome, the system comprising at least one lightning protection strip positioned on an inner wall of the radome, wherein the lightning protection strip defines, on the inner wall of the radome, a curve that is substantially perpendicular, at all points thereof, to the polarization direction of the electrical field vector radiated by an antenna across from the inner wall of the radome.

Abstract: An anti-lightning system for a composite structure having an external surface configured to be subjected to an air flow, the aforementioned system including at least one electrically conducting strip and fasteners attaching this strip to the aforementioned structure. According to the disclosed embodiments, with this structure including holes configured to accept the fastenings for the strip, at least some these fastenings comprise an attachment element that attaches the lightning to this structure. This attachment element is configured to be inserted in the hole with its upper part substantially flush with the external surface of the structure, this attachment element being in electrical contact with the electrically conducting strip. The electrically conducting strip is configured to be positioned on the opposite side of the structure to the external surface and electrically earthed.

Abstract: An aircraft latch including an operating lever; and adjustable means for adjusting an angle of inclination of the lever in a closed position of the latch, the means being controllable on the lever.

Abstract: An anti-lightning system for a composite structure having an external surface configured to be subjected to an air flow, the aforementioned system including at least one electrically conducting strip and fasteners attaching this strip to the aforementioned structure. According to the disclosed embodiments, with this structure including holes configured to accept the fastenings for the strip, at least some these fastenings comprise an attachment element that attaches the lightning to this structure. This attachment element is configured to be inserted in the hole with its upper part substantially flush with the external surface of the structure, this attachment element being in electrical contact with the electrically conducting strip. The electrically conducting strip is configured to be positioned on the opposite side of the structure to the external surface and electrically earthed.

Abstract: A device for detecting lightning strikes (9) on an electrically insulating structure (11) likely to be subjected to a lightning strike, for example an aircraft radome, includes on an external surface (12) one or more lightning arrester strips (10), made of an electrically conductive material and electrically linked to an electrically conductive structure. At least one inductive sensor (3) is positioned near the internal surface (13) of the electrically insulating structure so that the inductive sensor delivers a signal when a lightning arrester strip is passed through by a lightning current I. The signals from the inductive sensor, for example a flat coil or two flat coils mounted in opposition, are received and processed by acquisition means.

Abstract: A composite structure including two external skins and an internal core between them, wherein a portion of one of the external skins has to be replaced, with pressure from a counter-form and suction. The repair is accomplished by piercing a vent hole in the opposite external skin to discharge the air in the cells of the core, which improves adhesive bonding of the new portion on the core.

Abstract: A device for detecting lightning strikes (9) on an electrically insulating structure (11) likely to be subjected to a lightning strike, for example an aircraft radome, includes on an external surface (12) one or more lightning arrester strips (10), made of an electrically conductive material and electrically linked to an electrically conductive structure. At least one inductive sensor (3) is positioned near the internal surface (13) of the electrically insulating structure so that the inductive sensor delivers a signal when a lightning arrester strip is passed through by a lightning current I. The signals from the inductive sensor, for example a flat coil or two flat coils mounted in opposition, are received and processed by acquisition means.

Abstract: A method for through-repair of a composite material structure. Repair portions, established through two core layers, for example as a honeycomb and three polymer skins, including two external skins and a middle skin inserted between the core layers to obtain a composite structure, are set up and the polymer is hardened in vacuum. A counter-form is pressed onto one of the skins to guarantee a good aspect and surface quality. Vents are provided through the middle skin and possibly through the skin receiving the counter-form for proper degassing of the underlying cellular core.