Complex laminated composites may be repaired by removal of individual damaged plies through peeling in order to exploit the weaker interlaminar properties of these composites. Upon removal of the individual damaged plies through peeling, replacement plies may be added to restore the laminated composite. In addition, when damage extends through the thickness of a laminated composite, a plug may be used to allow plies to be replaced while maintaining contour within the repair region. A caul plate also may be used to stiffen and maintain the contour of a repair region while peeling and removing plies from the repair region.

Various method for repairing a tire tread are provided. In one embodiment, a method for repairing a tire tread comprises: providing a tire having a tire tread portion wherein the tire tread portion includes a tread element that is at least one of a tread block and a tread rib, and wherein the tread element includes a void resulting from wear or damage of the tire tread portion; removing a material from at least a portion of the tread element adjacent to the void to create a removed material portion, wherein the removed material portion includes a specific shape corresponding to a replacement element; applying an adhesive to at least one surface of the removed material portion; applying the replacement element to the removed material portion; and curing the adhesive.

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 non-acoustic panels are disclosed.

A method for mending damaged areas in fiber composite components formed from a plurality of unidirectional fiber layers includes the steps of automatically lifting at least one fiber layer of the fiber composite component at a cutting edge of the at least one fiber layer using a delaminating device, removing the at least one fiber layer in the extension direction of the fiber orientation of the at least one fiber layer, and separating off the removed at least one fiber layer in a defined manner at a separating edge defined by a separating device placed on the fiber composite component.

Disclosed is a method of repairing damage of an aircraft engine component made of or comprising weldable thermoplastic material, which method comprises welding of the weld filler material into an initially prepared damaged area. Also disclosed are the use of plastic welding technique for repairing damaged aircraft engine components made of weldable thermoplastic materials.

Complex laminated composites may be repaired by removal of individual damaged plies through peeling in order to exploit the weaker interlaminar properties of these composites. Upon removal of the individual damaged plies through peeling, replacement plies may be added to restore the laminated composite. In addition, when damage extends through the thickness of a laminated composite, a plug may be used to allow plies to be replaced while maintaining contour within the repair region. A caul plate also may be used to stiffen and maintain the contour of a repair region while peeling and removing plies from the repair region.

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.

A method of repairing a composite blade. The composite blade includes a metal work bonded to a composite part through an adhesive layer. The method includes determining a locally damaged portion of the metal work, and removing a bullet portion corresponding to the locally damaged portion. The method further includes detaching, debonding, and removing a first wing portion from the composite part to obtain a first exposed surface portion. The method further includes detaching, debonding, and removing a second wing portion from the composite part to obtain a second exposed surface portion. The method further includes reconditioning the first and second exposed surface portions to obtain first and second reconditioned surface portions, respectively, and applying first and second adhesive layers to the first and second reconditioned surface portions respectively. The method further includes bonding a metal work patch to the first and second adhesive layers.

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.

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.