Abstract: An apparatus and method is disclosed using a blanket (50) which is an assembly of at least one graphite fiber element of high thermal conductivity and at least one metal sheet element such as a copper sheet element to repair an aircraft structure (10) made of composite fiber materials. The blanket (50) is placed in thermal contact with a silicone rubber heat blanket (22), having an internal heat source, and the aircraft structure, such as composite laminates (12, 14). Use of the blanket (50) increases the rate at which the temperature of the laminates can be elevated to the proper range for repair and transfers heat from hot spots to cold spots to ensure a uniform temperature throughout the laminates.

Abstract: An apparatus and method is disclosed using a graphite fiber blanket (20) of high thermal conductivity to repair an aircraft structure (10) made of composite fiber materials. The graphite fiber blanket (20) is placed in thermal contact with a silicone rubber heat blanket (22), with an internal heat source, and the aircraft structure, such as composite laminates (12, 14). Use of the graphite fiber blanket (20) increases the rate at which the temperature of the laminates can be elevated to the proper range for repair and transfers heat from hot spots to cold spots to ensure a uniform temperature throughout the laminates.