The present invention provides a fuselage structure (1; 1′) of an aircraft comprising an annular skin segment (2; 2′) which has a cross-sectional opening (3; 3′), a pressure cap (4; 4′) for a pressure-tight closure of the cross-sectional opening (3; 3′), and a plurality of tension struts (7, 8, 9; 7′, 8′, 9′) which in each case connect the pressure cap (4; 4′) to the annular skin segment (2; 2′) and absorb loads acting on the pressure cap (4; 4′), as tensile loads. This advantageously means that the tension struts (7, 8, 9; 7′, 8′, 9′) do not have to absorb substantially any bending moments. Consequently, the tension struts can be produced with a relatively small cross section, which entails a reduction in weight. Furthermore, it is possible to produce and mount tension struts (7, 8, 9; 7′, 8′, 9′) of this type in a simple manner.