an apparatus and method is disclosed using a blanket 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 made of composite fiber materials . the blanket is placed in thermal contact with a silicone rubber heat blanket , having an internal heat source , and the aircraft structure , such as composite laminates . use of the blanket 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 .