The invention relates to an aircraft fuselage structure comprising at least first and second panels (1, 2) made of composite materials, placed side-by-side along a joint (6) and assembled together by means of at least one longitudinal joint (20), said longitudinal joint comprising a double Ω-shaped runner comprising: first and second Ω-shaped elements (21, 22), each including a head (21a, 22a) and two webs (21b, 21c, 22b, 22c); a first lateral flange (24) positioned as a continuation of the first web (21b) of the first Ω-shaped element; a second lateral flange (25) positioned as a continuation of the last web (22c) of the second Ω-shaped element; and a central flange (23) connecting the second web (21c) of the first Ω-shaped element with the first web (22b) of the second Ω-shaped element and covering the joint between the two panels.
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