| 摘要 |
The invention relates to the structure of the load-introduction area in the fuselage rear section of an aircraft, including elements (3, 4) for receiving loads from the horizontal and vertical tailplanes connected to structural elements (2, 8, 9), in which: (a) the structural elements are the skin (8), two contiguous load ring frames (2) having a cross-section in the form of p or omega and at least a third ring frame (9); (b) the element receiving the load from the horizontal tailplane is a first fitting (3) structured as a torsion box disposed transversely between the aforementioned load ring frames (2) and connected to same, and the elements receiving the loads from the vertical tailplane are second fittings (4) coupled to the aforementioned ring frames (2, 9); (c) and the ring frames (2, 9) and the first and second fittings (3, 4) are made fully from composite material.
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