An automatic machine for repairing plastic sheets having incorporated in a support structure (3): a rotary head (4), with several work stations with cutting device (5) for cutting the edge of a sheet (2), donor pellet supply device (6, 7), welding device (8) for welding the donor pellet, and pressing device (9) for pressing the weld thus made; an outer bench (10) for situating the sheet (2) to be repaired on same; donor pellet fastening device (11); sheet fastening device for holding the sheet (2); andoperation control device connected to a programmable logic controller.

An automatic machine for repairing plastic sheets having incorporated in a support structure (3): a rotary head (4), with several work stations with cutting device (5) for cutting the edge of a sheet (2), donor pellet supply device (6, 7), welding device (8) for welding the donor pellet, and pressing device (9) for pressing the weld thus made; an outer bench (10) for situating the sheet (2) to be repaired on same; donor pellet fastening device (11); sheet fastening device for holding the sheet (2); andoperation control device connected to a programmable logic controller.

Systems and methods for attaching to a surface and applying a calibrated load are described. An example system for attaching to a surface and applying a calibrated load includes a suction cup to attach to an attachment surface and a rocker arm to apply a load to a working surface. The rocker arm is coupled to the suction cup and comprises a portion extending over the suction cup to apply pressure over the suction cup. The system also includes a force scale coupled to the rocker arm to provide an indication of an amount of the load applied to the working surface by the rocker arm.

A method of repairing or reinforcing, or attaching an accessory part to a wind turbine blade includes: determining a criterion to be satisfied by a repair member including a reinforcing fiber and a UV curable resin, the criterion being an adhesion strength of the repair member relative to a base member of the wind turbine blade; determining a work condition including: dimensions of the repair member, the number of the layers of the reinforcing fiber in the repair member, and/or a fiber extension direction of the reinforcing fiber, based on a damage condition of a repair target portion of the wind turbine blade; placing the reinforcing fiber and UV curable resin on the repair target portion based on the determined work condition; and obtaining the repair member by curing the UV curable resin so that the adhesion strength of the repair member relative to the base member satisfies the criterion.

A composite part is cured out-of-autoclave using an inductively heated, stand-alone tooling. The part in placed on a tool and is covered by a heating blanket. One side of the part is heated by inductive coil circuits in the tool, and the other side of the part is heated by inductive coil circuits in the blanket.

A composite part is cured out-of-autoclave using an inductively heated, stand-alone tooling. The part in placed on a tool and is covered by a heating blanket. One side of the part is heated by inductive coil circuits in the tool, and the other side of the part is heated by inductive coil circuits in the blanket.

A method of forming a build in a powder bed includes emitting a plurality of laser beams from selected fibers of a diode laser fiber array onto the powder bed, the selected fibers of the array corresponding to a pattern of a layer of the build; and simultaneously melting powder in the powder bed corresponding to the pattern of the layer of the build. An apparatus for forming a build in a powder bed includes a diode laser fiber array including a plurality of diode lasers and a plurality of optical fibers corresponding to the plurality of diode lasers, each optical fiber configured to receive a laser beam from a respective diode laser and configured to emitting the laser beam; a support configured to support a powder bed or a component configured to support the powder bed at a distance from ends of the optical fibers; and a controller configured to control the diode laser fiber array to emit a plurality of laser beams from selected fibers of the diode laser fiber array onto the powder bed, the selected fibers of the array corresponding to a pattern of a layer of the build and simultaneously melt the powder in the powder bed corresponding to the pattern of the layer of the build.

A method of forming a build in a powder bed includes emitting a plurality of laser beams from selected fibers of a diode laser fiber array onto the powder bed, the selected fibers of the array corresponding to a pattern of a layer of the build; and simultaneously melting powder in the powder bed corresponding to the pattern of the layer of the build. An apparatus for forming a build in a powder bed includes a diode laser fiber array including a plurality of diode lasers and a plurality of optical fibers corresponding to the plurality of diode lasers, each optical fiber configured to receive a laser beam from a respective diode laser and configured to emitting the laser beam; a support configured to support a powder bed or a component configured to support the powder bed at a distance from ends of the optical fibers; and a controller configured to control the diode laser fiber array to emit a plurality of laser beams from selected fibers of the diode laser fiber array onto the powder bed, the selected fibers of the array corresponding to a pattern of a layer of the build and simultaneously melt the powder in the powder bed corresponding to the pattern of the layer of the build.

A processing apparatus such as a heating and/or debulking apparatus that may be used to debulk a plurality of uncured composite layers to form an article such as an aircraft component may include a plurality of interconnected smart susceptor heater blankets. The plurality of smart susceptor heater blankets may be connected in series or in parallel, and may be controlled to uniformly heat the component during formation.

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.