Abstract: An assembly includes a bag and of a composite panel exhibiting a damaged region to be repaired by polymerization of a repair piece using the bag. The bag includes a sheet intended to be laid over the panel. When the panel and the sheet are laid one atop of the other, the sheet exhibits regions capable of absorbing heat emitted by radiation onto it in a proportion that is dependent on the polymerization temperature needed for that region of the panel that corresponds to it, the radiation being partially absorbed by suitable colouration of the sheet in the region concerned. Determining those regions of the panel in which radiation is less well absorbed than in others means that the heating can be adapted to suit the needs of polymerization in terms of repair and that even polymerization can thus be obtained over the entire damaged region, thereby consolidating the repair.

Abstract: A bumper for a vehicle, comprising at least one part made of resilient material, having a curved front portion forming an inner cavity. The front portion has apertures enabling the cavity to be put into communication with the exterior of the resilient part. At least one marking fluid cell is provided inside the cavity. A fastener is provided to fasten the one part to the vehicle.

Abstract: A vehicle bumper comprising at least one part made of resilient material, in the interior of which there is provided at least one marking fluid cell with an opening to the exterior. The opening is closed by a closure device which, under the effect of a pressure applied with a determined intensity, can open up the opening, allowing the marking fluid to access the exterior of the cell through which the marking fluid can flow, and also comprising a securing element configured to secure the at least one part on the vehicle.

Abstract: An assembly includes a bag and of a composite panel exhibiting a damaged region to be repaired by polymerization of a repair piece using the bag. The bag includes a sheet intended to be laid over the panel. When the panel and the sheet are laid one atop of the other, the sheet exhibits regions capable of absorbing heat emitted by radiation onto it in a proportion that is dependent on the polymerization temperature needed for that region of the panel that corresponds to it, the radiation being partially absorbed by suitable colouration of the sheet in the region concerned. Determining those regions of the panel in which radiation is less well absorbed than in others means that the heating can be adapted to suit the needs of polymerization in terms of repair and that even polymerization can thus be obtained over the entire damaged region, thereby consolidating the repair.

Abstract: A method for repairing a structure comprising at least one zone to be heated and which comprises the steps of inflating a frame to form a framework, attaching panels removably to the frame to form an enclosure referred to as a heating enclosure, positioning the enclosure over the zone, heating the interior space of the enclosure using a heating device.

Abstract: A bumper for a vehicle, comprising at least one part made of resilient material, having a curved front portion forming an inner cavity. The front portion has apertures enabling the cavity to be put into communication with the exterior of the resilient part. At least one marking fluid cell is provided inside the cavity. A fastener is provided to fasten the one part to the vehicle.

Abstract: A vehicle bumper comprising at least one part made of resilient material, in the interior of which there is provided at least one marking fluid cell with an opening to the exterior. The opening is closed by a closure device which, under the effect of a pressure applied with a determined intensity, can open up the opening, allowing the marking fluid to access the exterior of the cell through which the marking fluid can flow, and also comprising a securing element configured to secure the at least one part on the vehicle.

Abstract: A method and tool for repairing a damaged zone of an aircraft radome, using the actual radome itself as a heating chamber to avoid resorting to an autoclave and the removal of certain parts of the radome which cannot withstand the curing temperature needed for the repair. The method for repairing a radome, wherein the radome comprises a composite panel exhibiting a double curvature forming a dome, the panel comprising at least one damaged zone, comprises the steps of closing an interior space of the panel using a cap to form a repair chamber. The surface of the panel forms the repair chamber containing the damaged zone. Another step is heating the space inside the repair chamber to form a heating chamber allowing the curing expected for repairing the damaged zone.

Abstract: A method and a tool for repairing a composite-material panel of an aircraft with at least one repair part made of composite material without using an autoclave. The repair method includes the steps of preparing the panel, placing at least one repair part made of composite material on the second face to cover a damaged zone, positioning a vacuum bag configured to sealingly cover the repair part, polymerizing or consolidating the repair part, compressing the vacuum bag against the repair part using a compression plate concomitantly with the step in which the repair part is polymerized or consolidated.

Abstract: A method for repairing a structure comprising at least one zone to be heated and which comprises the steps of inflating a frame to form a framework, attaching panels removably to the frame to form an enclosure referred to as a heating enclosure, positioning the enclosure over the zone, heating the interior space of the enclosure using a heating device.

Abstract: A method and tool for repairing a damaged zone of an aircraft radome, using the actual radome itself as a heating chamber to avoid resorting to an autoclave and the removal of certain parts of the radome which cannot withstand the curing temperature needed for the repair. The method for repairing a radome, wherein the radome comprises a composite panel exhibiting a double curvature forming a dome, the panel comprising at least one damaged zone, comprises the steps of closing an interior space of the panel using a cap to form a repair chamber. The surface of the panel forms the repair chamber containing the damaged zone. Another step is heating the space inside the repair chamber to form a heating chamber allowing the curing expected for repairing the damaged zone.

Abstract: A method and a tool for repairing a composite-material panel of an aircraft with at least one repair part made of composite material without using an autoclave. The repair method includes the steps of preparing the panel, placing at least one repair part made of composite material on the second face to cover a damaged zone, positioning a vacuum bag configured to sealingly cover the repair part, polymerizing or consolidating the repair part, compressing the vacuum bag against the repair part using a compression plate concomitantly with the step in which the repair part is polymerized or consolidated.