FIELD: transport.
SUBSTANCE: invention relates to aircraft engineering. Aircraft fuselage comprises frames 1 with outer skin 2, stringers 3 jointed with skin 2 and frames 1, and passenger cabin floor beams 4 located nearby fuselage neutral surface, cargo floor transverse beams 5 and transverse ceiling beams 6. Fuselage cross section at top and bottom sections is formed by equal large-radius circular arcs while at side section it is formed by smaller-radius arcs. Frames 1 are divided into side, top and bottom zones with different stiffness. Cargo floor transverse beams 5 are arranged on one side to allow positioning containers and, on the other side, said beams are arranged in zones wherein larger-radius circular arcs change into smaller-radius circular arcs. Transverse ceiling beams 6 are located in zone wherein larger-radius circular arc changes into smaller-radius circular arc of side surface. Cabin floor beams 4 located nearby fuselage neutral surface.
EFFECT: reduced weight.
5 cl, 3 dwg
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