A method is provided during which a composite preform is provided that includes an electric heater, fiber-reinforcement and thermoset material. The composite preform is consolidated to provide a composite aircraft component. The consolidating includes heating the thermoset material using the electric heater to cure the thermoset material. The electric heater and the fiber-reinforcement are embedded within the cured thermoset material. The electric heater is configured as a part of a thermal anti-icing system for melting and/or preventing ice accumulation on an exterior surface of the composite aircraft component.

A method for repairing a target member including a ceramic matrix composite reinforced by ceramic fiber includes: a removal step of removing at least a part of a surface of the target member; an arrangement step of arranging a green body for repair which includes the ceramic fiber on a portion where the surface is removed in the removal step; an impregnation step of impregnating at least the portion of the target member where the green body for repair is disposed with slurry; and a sintering step of sintering the target member on which the green body for repair is disposed, after the impregnation step.

A method for repairing a target member including a ceramic matrix composite reinforced by ceramic fiber includes: a removal step of removing at least a part of a surface of the target member; an arrangement step of arranging a green body for repair which includes the ceramic fiber on a portion where the surface is removed in the removal step; an impregnation step of impregnating at least the portion of the target member where the green body for repair is disposed with slurry; and a sintering step of sintering the target member on which the green body for repair is disposed, after the impregnation step.

A method for repairing a composite structure is provided. A rework zone is defined on the composite structure. A theoretical scarfing bottom surface is identified for the rework zone from a model of the composite structure. An actual scarfing bottom surface in a local axis system is identified for the rework zone. Parameters for a rework program for an automated scarfing tool are modified based on deviations between the theoretical scarfing bottom surface and the actual scarfing bottom surface. Plies in the rework zone are removed using the automated scarfing tool.

A method of modifying or repairing a fluid conduit assembly includes scanning a sealing feature of a fluid conduit, the sealing feature including an abnormality, creating a 3D model of a sealing member configured to provide a fluid seal with the sealing feature, and utilizing the 3D model to form the sealing member via additive manufacturing. The method may include modifying the sealing feature of the fluid conduit to reduce or remove the abnormality and provide the sealing feature with modified dimensions. Scanning the sealing feature may include determining the modified dimensions of the sealing feature.

An applicator repair system for an additive manufacturing (AM) system, and an AM system including the same are disclosed. The applicator repair system includes a repair device including a repair element configured to repair a damaged applicator element on an applicator of an AM system. The damaged applicator element is configured to distribute a layer of raw material on a build platform of the AM system. The repair device is positioned within a processing chamber of the AM system. A damaged applicator controller may be provided that is configured to cause repair of the damaged active applicator in response to the damaged applicator being identified as damaged.

An applicator repair system for an additive manufacturing (AM) system, and an AM system including the same are disclosed. The applicator repair system includes a repair device including a repair element configured to repair a damaged applicator element on an applicator of an AM system. The damaged applicator element is configured to distribute a layer of raw material on a build platform of the AM system. The repair device is positioned within a processing chamber of the AM system. A damaged applicator controller may be provided that is configured to cause repair of the damaged active applicator in response to the damaged applicator being identified as damaged.

A method of repairing damage to a composite material having a composite substrate and at least one layer of shielding material includes: a) removing damage to the at least one layer of shielding material by creating a hole in the at least one layer of shielding material; b) applying a patch of shielding material in the region of the hole via a resin, wherein a ratio of a resin weight to a weight of the patch of shielding material lies in a range between about 0.45-0.55; and c) curing the resin, wherein an absorptive, consumable material is positioned in contact with the resin during at least a portion of the curing.

A method of repairing damage to a composite material having a composite substrate and at least one layer of shielding material includes: a) removing damage to the at least one layer of shielding material by creating a hole in the at least one layer of shielding material; b) applying a patch of shielding material in the region of the hole via a resin, wherein a ratio of a resin weight to a weight of the patch of shielding material lies in a range between about 0.45-0.55; and c) curing the resin, wherein an absorptive, consumable material is positioned in contact with the resin during at least a portion of the curing.

Disclosed herein is a method of repairing surface damage in an exterior surface of a hollow bladder, made of a cured elastomer. The method comprises placing first strips, made of an uncured elastomer, at least partially within the surface damage in the exterior surface of the hollow bladder in a side-by-side arrangement. The method also comprises sealing the surface damage, the first strips, and a portion of the exterior surface surrounding the surface damage in a vacuum bag. The method further comprises reducing pressure within the vacuum bag relative to outside the vacuum bag. The method additionally comprises while the pressure within the vacuum bag is reduced, heating the first strips from within the vacuum bag to cure the first strips.