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.

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.

A method of repairing a core stiffened structure, including removing a damaged portion of the core stiffened structure; bonding a shelf onto a first core member; bonding a second core member to a shelf; and securing a skin patch over the second core member.

A blade for an aircraft gas turbine engine includes, in a longitudinal direction, a blade root, a shank and an aerofoil body, the aerofoil body extending in the longitudinal direction between the shank and a blade tip and in a transverse direction between a leading edge made of metal material and a trailing edge. The blade includes a blade core made of composite material having a three-dimensional woven fibrous reinforcement forming the blade root, the shank and a part of the aerofoil body. The blade also includes a skin made of composite material having a two-dimensional woven fibrous reinforcement surrounding the aerofoil body part of the blade core, the skin being interposed between the leading edge made of metal material and a front edge of the aerofoil body part of the blade core to define a thinned leading edge portion, the skin including one or more two-dimensional woven plies.

A method for recovering vinyl window frames. The method of recovering vinyl window frames includes identifying damages in an existing vinyl frame having a plurality of planes, wherein the damages exist in at least one plane, measuring the area of the frame to be covered, creating a template of the frame by securing pre-cut plates together with a gap between to allow for bending along the gap, such that the template can conform to the frame, marking cuts to be made to the replacement cover using the template, cutting the replacement cover to duplicate the existing frame, and applying the replacement cover over the existing vinyl frame.

A repair and reinforcement method for an aircraft is provided. The method includes cleaning a corroded portion of a structure of the aircraft, applying an adhesive layer to the cleaned portion of the structure and forming a polymer matrix composite (PMC) patch for application to the adhesive.

A repair and reinforcement method for an aircraft is provided. The method includes cleaning a corroded portion of a structure of the aircraft, applying an adhesive layer to the cleaned portion of the structure and forming a polymer matrix composite (PMC) patch for application to the adhesive.

A method for repairing a damaged area of a stealth composite structure having a stealth function using a scarf patch includes the steps of diagnosing the damaged area; deriving a repair area including the diagnosed damaged area; processing the scarf patch according to the derived repair area; machining a patch hole according to the derived repair area to remove the damaged area; and coupling the scarf patch to the patch hole so that an inner wall of the patch hole and a side surface of the scarf patch face.

A method for repairing a damaged area of a stealth composite structure having a stealth function using a scarf patch includes the steps of diagnosing the damaged area; deriving a repair area including the diagnosed damaged area; processing the scarf patch according to the derived repair area; machining a patch hole according to the derived repair area to remove the damaged area; and coupling the scarf patch to the patch hole so that an inner wall of the patch hole and a side surface of the scarf patch face.

Apparatus and methods for manufacturing and repairing fibre-reinforced composite materials are disclosed. In various embodiments, the apparatus and methods disclosed herein use a resin retaining/releasing device comprising resin having a viscosity that is temperature dependent for infusion into a region of a part. The resin retaining/releasing device may include a first sheet and an opposite second sheet at least partially enclosing the quantity of resin. The first sheet and the second sheet may be gas-permeable. The second sheet may be substantially resin-impermeable when the viscosity of the resin is above a threshold viscosity and resin-permeable when the viscosity of the resin is below the threshold viscosity.