Patent ID: 8617687

Claim:
A structure comprising: a composite structure configured for use in or on an aircraft, the composite structure selected from the group consisting of: a stringer of the aircraft, a floor panel of the aircraft, a cryogenic tank installed on the aircraft, a spar of the aircraft, and a rib of the aircraft; a filler material disposed within and abutting all first inner walls of the composite structure; a first barrier material secured to second inner walls of the filler material, the second inner walls being further within the composite structure relative to the first inner walls, and third inner walls of the first barrier material defining a first channel inside the composite structure; and a second barrier material secured to fourth inner walls of the filler material, the fourth inner walls being further within the composite structure relative to the first inner walls, and fifth inner walls of the second barrier material defining a second channel inside the composite structure; wherein at least one of a number of fiber optic cables, a number of power lines, a number of wires, and a number of data lines is located in one of the first channel and the second channel.