A method of repairing a composite structure includes providing an assembled composite structure comprising a substantially rigid outer component, wherein the composite structure comprises a void space at least partially bounded by the outer component. The method further includes forming an injection hole through the outer component to provide a path between the void space and space external to the composite structure. The method further includes injecting foam into the void space through the injection hole while the foam is in a substantially unexpanded state and expanding the foam within the void space.

A method of repairing an aircraft component having a structural core surrounded by an exterior skin of composite material includes removing damaged material from the component to create a cavity therein that exposes an undamaged portion of the structural core, applying a septum comprising composite material to the undamaged portion of the structural core within the cavity such that an orientation of fibers in the septum matches an orientation of fibers in the exterior skin, placing a repair core onto the septum in the cavity such that cells of the repair core are in alignment with cells of the undamaged portion of the structural core, inserting a shim into the cavity along a perimeter of the repair core, applying a patch that covers the cavity to the exterior skin, and co-curing the septum, shim, and patch to bond the repair core in place within the cavity.

A method of repairing an aircraft component having a structural core surrounded by an exterior skin of composite material includes removing damaged material from the component to create a cavity therein that exposes an undamaged portion of the structural core, applying a septum comprising composite material to the undamaged portion of the structural core within the cavity such that an orientation of fibers in the septum matches an orientation of fibers in the exterior skin, placing a repair core onto the septum in the cavity such that cells of the repair core are in alignment with cells of the undamaged portion of the structural core, inserting a shim into the cavity along a perimeter of the repair core, applying a patch that covers the cavity to the exterior skin, and co-curing the septum, shim, and patch to bond the repair core in place within the cavity.

The present invention is directed to a process for resurfacing a damaged surface of plastic lenses, such as vehicle headlights and taillights to restore the plastic lens surface to its original clarity and transparency. During process, a cleaned damaged surface is preferably orbital sanded with a moistened sand paper disc mounted on a sander for removing visible scratches and yellowing of the moistened damaged surface of the plastic lens. Thereafter, the sanded surface is preferably rotary polished with the slush-resistant polishing composition of the present invention applied on a polishing pad mounted on an polisher for removing any visible score marks that may have been created during the sanding step. Then, the polished surface is preferably rotary finished with the slush-resistant finishing composition of the present invention applied on a finishing pad mounted on a finisher for removing any visible swirls marks that may have been created during the polishing step.

A method is provided for managing the temperature of heat sensitive material located near a repair patch being thermally cured on a composite skin using a heating blanket. The method comprises configuring an assembly of thermally conductive cooling blocks to fit within a space between the heating blanket and the heat sensitive material. The assembly of thermally conductive cooling blocks is then installed against the skin within the space, forming a heat sink that conducts a portion of heat out of the composite skin away from the heat sensitive material.

A method is provided for managing the temperature of heat sensitive material located near a repair patch being thermally cured on a composite skin using a heating blanket. The method comprises configuring an assembly of thermally conductive cooling blocks to fit within a space between the heating blanket and the heat sensitive material. The assembly of thermally conductive cooling blocks is then installed against the skin within the space, forming a heat sink that conducts a portion of heat out of the composite skin away from the heat sensitive material.

An aerial drone for repairing holes or punctures in a membrane on a roof, characterized in that the aerial drone comprises at least one camera for recording a section of the membrane, an applicator adapted to apply material onto the section of the membrane, wherein the applicator is controllable wirelessly from a different altitude and/or the ground.

A ceramic matrix composite member including a ceramic matrix composite reinforced by ceramic fiber, includes a body portion and a joint portion joined integrally to the body portion, the joint portion occupying a part of a surface of the ceramic matrix composite member, wherein the body portion includes at least one hole extending toward an inside of the body portion from a boundary surface between the body portion and the joint portion, and the at least one hole is filled with a matrix of the ceramic matrix composite, wherein the body portion includes a first region where a density of the ceramic fiber is relatively high and a second region where the density of the ceramic fiber is lower than that in the first region, and wherein the at least one hole exists so as to cut off a part of bundles of the ceramic fiber in the second region.

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 conditioning agent (typically for use in repairing a flaw in a glazing panel) is contained in a sealed container which is itself disposed internally of a flexible outer walled container. Pressure applied to the outer flexible walled container can cause release of the conditioning agent from the internal conditioning agent container. The conditioning agent preparation may comprise a hygroscopic solvent (such as acetone) combined with one or more primer additives to prime the surface of the glazing panel for repair.