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.
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