A method for repairing a component constructed in multiple layers from a layer composite material comprises a step of removing material of the layer composite material of the component in the region of damage to the component in order to form a scarfed cutout, such that a scarfed peripheral contour formed from a plurality of layers of the component is formed. Furthermore, fiber-reinforced plastic strips, which exhibit a curable plastic material in an uncured state, are applied in layers in the cutout in order to create a replacement-structure semifinished product that is complementary to and butts against the scarfed peripheral contour of the component. In a further step, the curable plastic material contained in the fiber-reinforced plastic strips is cured in order to create a replacement structure and for joining the replacement structure to the component.

To reduce the processing time in the case of repairing of excessively countersunk bolt openings or surface damage in fiber composite workpieces, it is proposed to countersink the corresponding surface spot to produce a contact surface and a depression for a fiber composite insert body. The fiber composite insert body is placed onto the contact surface and is fixed on the fiber composite workpiece in the depression. In the case of an excessively countersunk bolt opening, a new bolt opening is drilled into the fiber composite insert body, which new bolt opening is subsequently countersunk to the correct countersunk bore depth. In the case of the method, a three-legged application tool can be used which positions and orients the fiber composite insert body correctly and presses it onto the fiber composite workpiece during the curing of the adhesive.

Systems and methods are provided for cleaning composite fabrication machinery. One embodiment is a method for cleaning of a composite application machine, comprising: displacing an anvil of a head of an Automated Fiber Placement (AFP) machine from an operation location relative to a cutter, cleaning at least one of the cutter and the anvil, and relocating the anvil to the operation location relative to the cutter.

Methods for repairing composite cylindrical components are provided. One exemplary method for repairing a cylindrical component defining an axial direction, a radial direction, and a circumferential direction includes removing a damaged region of the cylindrical component. A flange extending from a cylindrical body of the cylindrical component is included in the damaged region. One or more arc segments that extend along the circumferential direction are connected with the existing cylindrical component. At least one of the arc segments includes a prefabricated flange. One or more plies are laid up to connect the arc segments with the existing cylindrical component to repair the damaged region of the cylindrical body and the prefabricated flange formed integrally with one of the arc segments replaces the damaged portion of the flange. Repaired cylindrical components are also provided.

In a method and a device for recycling a thermoplastic fibre-reinforced composite material, which is in at least one deposition layer in a component (1), it is suggested that said fibre-reinforced composite material should be pulled off from the remaining component (1), in the direction of a main fibre direction, in at least one pull-off layer (10) comprising fibres and matrix material.

Disclosed herein is a method of repairing a composite structure comprising fiber-reinforced polymer plies each with unidirectional fibers. The method comprises removing a damaged portion of the composite structure to form a void in the composite structure. The method also comprises positioning an adhesive layer into the void. The method further comprises positioning a first nanotube sheet ply and a first fiber-reinforced polymer repair ply into the void, by first positioning one of the first nanotube sheet ply or the first fiber-reinforced polymer repair ply into the void over the adhesive layer. The first nanotube sheet ply is fiberless and the first fiber-reinforced polymer repair ply comprises unidirectional fibers.

Methods for reworking structures and reworked cellular core panels, reworked structures comprising the reworked cellular core panels, and guides and cutting apparatuses for reworking cellular acoustic panels and reworking cellular acoustic and non-acoustic panels are disclosed.

A method (1800) of debonding a first layer (404) from a second layer (408), wherein the first layer (404) is bonded to the second layer (408) by an adhesive (410) located between the first and second layers, comprises: inserting (1804) a blade (602) of a cleaving tool (600) between the first and second layers (404, 408); and exerting (1806) a controlled force on the cleaving tool (600) to move the cleaving tool so as to de-bond the first and second layers (404, 408) in a region, wherein the force exerted is controlled to match a de-bonding force calculated for the region, and such that the movement of the cleaving tool (600) stops if the calculated force is less than force required to move the cleaving tool (600) and continued if the calculated force is higher than or equal to the force required to move the cleaving tool.

Provided is a method for repairing a root of a rotor blade of a wind turbine, the root including several bores for receiving a bolt and extending form the root front surface into the blade, wherein at least a part of the front surface blade material surrounding the bore is removed using a removing tool and that at least one shim plate is attached to the processed front surface surrounding the bore.

An acoustic honeycomb panel is plugged with an acoustic honeycomb plug. The acoustic honeycomb plug is adhesively bonded in the panel using a honeycomb seam. The honeycomb seam is composed of a honeycomb support that is located within the seam channel and an adhesive. Using honeycomb seams to adhesively bond acoustic honeycomb plugs into acoustic honeycomb panels is useful in repairing damaged areas of acoustic honeycomb panels that are located in the acoustic treatments for jet engines.