FIELD: aircraft engineering.
SUBSTANCE: invention refers to the manufacturing of the reinforced fuselage of the aircraft (AC) by means of using the vertically oriented circumferential stiffeners. Aircraft comprises the plurality of circumferential grooved stiffeners with the continuous grooved pattern, which are located inside the fuselage of the aircraft and substantially normally configured in relation to the longitudinal axis of the aircraft. Aircraft also comprises the casing, which is connected to the plurality of circumferential grooved stiffeners, each of the circumferential grooved stiffeners comprises the upper section and the lower section. In this case, each upper section of the stiffener is adjacent to the lower section of the adjacent circumferential grooved stiffener.
EFFECT: ensuring the hardening of the aircraft, the weight reduction of the structure are achieved.
20 cl, 8 dwg
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