| 摘要 |
The aircraft fuselage part (31) located in a section of an aircraft (11) having attached a propulsion system (13) by means of upstream pylons (17) that comprises: a skin (35); a plurality of frames (37) arranged perpendicularly to the longitudinal axis (33), a single or internally divided upper longitudinal box (41) and a single or internally divided lower longitudinal box (51) which are configured to form with the skin (35) a multi-cell structure, belonging in each cell the external side to the skin (35) and the internal sides to said longitudinal boxes (41, 51); a plurality of lateral beams (61) that are interconnected with said frames (37) to form together with the skin (35) a structural unity. Said fuselage components (35, 37, 41, 51, 61) are dimensioned so that the aircraft can withstand the effect of pre-defined failure events keeping a sufficient number of closed cells.
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