Fuselage is the main element of unmanned aerial vehicle, which parameters optimization could increase the structure strength and weight characteristics. Both the modern polymer composite materials with high specific characteristics and the advanced power circuits are able to assist in solving this problem. Selection and optimization of the structural power scheme of the unmanned aerial vehicle fuselage appear to be an urgent task. Structure loads under various flight and maneuver modes were analyzed. Eight fuselage structural power schemes were designed including classic, grid, auxetic and biosimilar structures. Operation of the power circuits made of carbon fiber exposed to the obtained loads was considered, and their stress-strain state was determined. Rational scheme was selected according to the minimum mass and maximum strength criteria, for which the main parameters were determined. Advantage of the promising power circuit over the classical one was shown. The results obtained are part of a comprehensive study of the promising structural power schemes made of polymer composite materials.