A method for repairing a laminated article having a damaged area comprising the steps of: removing the damaged area from the laminated article so as to leave a repair site; positioning a repair patch to cover the repair site; placing one or more heat blankets over the repair patch and other selected locations; placing the laminated article with the repair patch in a vacuum bag; placing the vacuum bag in an autoclave; operating the autoclave within a selected range of desired temperatures and pressures; and, curing the repair patch of the laminated article without disturbing or damaging the adjacent bondments within a composite structure.

A method for repairing a laminated article having a damaged area comprising the steps of: removing the damaged area from the laminated article so as to leave a repair site; positioning a repair patch to cover the repair site; placing one or more heat blankets over the repair patch and other selected locations; placing the laminated article with the repair patch in a vacuum bag; placing the vacuum bag in an autoclave; operating the autoclave within a selected range of desired temperatures and pressures; and, curing the repair patch of the laminated article without disturbing or damaging the adjacent bondments within a composite structure.

In a method for processing a fiber compound structure, an unhardened fiber layer is arranged on a surface section of the fiber compound structure. A pressure cushion is arranged above the surface section. The pressure cushion has a pressure cap and a pressure-tight cap mat pressure-tightly connected to a circumferential border of the pressure cap such that the cap mat limits a pressure area together with the pressure cap. An overpressure in the pressure area is generated. The pressure cushion is pressed onto the fiber compound structure such that the overpressure presses the cap mat against the fiber layer while supporting the fiber compound structure on a side of the fiber compound structure that is opposed to the surface section. The fiber layer is hardened

In a method for processing a fiber compound structure, an unhardened fiber layer is arranged on a surface section of the fiber compound structure. A pressure cushion is arranged above the surface section. The pressure cushion has a pressure cap and a pressure-tight cap mat pressure-tightly connected to a circumferential border of the pressure cap such that the cap mat limits a pressure area together with the pressure cap. An overpressure in the pressure area is generated. The pressure cushion is pressed onto the fiber compound structure such that the overpressure presses the cap mat against the fiber layer while supporting the fiber compound structure on a side of the fiber compound structure that is opposed to the surface section. The fiber layer is hardened

A repair method is provided during which a thermoplastic patch is arranged on a thermoplastic aircraft component. The thermoplastic patch and the thermoplastic aircraft component each include a thermoplastic matrix and a plurality of fibers embedded within the thermoplastic matrix. A metal plate is arranged against a stack. The stack includes the thermoplastic patch and the thermoplastic aircraft component. The thermoplastic patch and the thermoplastic aircraft component are consolidated together. The consolidating includes concurrently induction heating the thermoplastic patch, the thermoplastic aircraft component and the metal plate using an induction heating coil.

A repair method is provided during which a thermoplastic patch is arranged on a thermoplastic aircraft component. The thermoplastic patch and the thermoplastic aircraft component each include a thermoplastic matrix and a plurality of fibers embedded within the thermoplastic matrix. A metal plate is arranged against a stack. The stack includes the thermoplastic patch and the thermoplastic aircraft component. The thermoplastic patch and the thermoplastic aircraft component are consolidated together. The consolidating includes concurrently induction heating the thermoplastic patch, the thermoplastic aircraft component and the metal plate using an induction heating coil.

An inverted double dome double vacuum debulk tool having separable upper and lower chamber portions which can be assembled to form a vacuum chamber. In accordance with some embodiments, the top and bottom halves each comprise a circular cylindrical sidewall closed at one end by an inverted dome. The domes may be hemispherical or semi-elliptical with convex sides facing the chamber interior space. A base plate on which the composite patch rests is removable from the vacuum chamber. Various fittings pass electrical power and vacuum into the tool and sensor outputs out of the tool.

In a method for processing a fibre compound structure, an unhardened fibre layer is arranged on a surface section of the fibre compound structure. A pressure cushion is arranged above the surface section. The pressure cushion has a pressure cap and a pressure-tight cap mat pressure-tightly connected to a circumferential border of the pressure cap such that the cap mat limits a pressure area together with the pressure cap. An overpressure in the pressure area is generated. The pressure cushion is pressed onto the fibre compound structure such that the overpressure presses the cap mat against the fibre layer while supporting the fibre compound structure on a side of the fibre compound structure that is opposed to the surface section. The fibre layer is hardened

A method of joining a first element in composite material with a second element in composite material to define a structural component of an aircraft comprising arranging the first element in contact on the second element; applying a non-rigid heating layer on the first element; applying a layer of shape memory thermoplastic polymer, pre-loaded in a compressed non-equilibrium condition, onto the heating layer; applying a vacuum bag to the assembly thus obtained; sealing the vacuum bag to define a vacuum chamber housing the first element, at least part of the second element, the heating layer and the shape memory layer; applying vacuum inside the vacuum chamber; applying heat to the first element, to the second element and to the shape memory layer by activating the heating layer; expanding the shape memory layer from the compressed non-equilibrium condition to an expanded equilibrium condition by means of the step of applying heat.

An assembly and method for repairing a pipeline. The assembly may include a sleeve positioned between a bladder and a liner. The sleeve includes a first portion having a larger diameter than a second portion. The larger diameter at the first portion of the sleeve allows the sleeve to expand outward with less pressure. Upon the introduction of fluid pressure into the bladder, the bladder, sleeve, and liner expand radially outward at the first portion of the sleeve first. Then, as pressure inside the bladder increases, the remainder of the assembly expands radially outward toward the pipe in a serial fashion longitudinally away from the first portion. In this manner the user can control which area of the assembly is inflated and expanded first by positioning the first portion of the sleeve at the appropriate location.