FIELD: transport.
SUBSTANCE: invention relates to aircraft engineering. Proposed aircraft structure comprises skin panel with dual shell, skin single-piece panel, stiffness element arranged between skin panels and lengthwise strip to load transition section. said lengthwise trap is located in the area of lengthwise seam and comprises first and second lengthwise flanges shifted relative to each other and jointed together by strap. Load transition section is located in the area of transverses seam for connection of lengthwise stiffness element at skin single-piece panel with dual-shell panel.
EFFECT: decreased weight of aircraft skin.
20 cl, 6 dwg
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