FIELD: transport.
SUBSTANCE: invention relates to aircraft engineering, particularly, to aircraft fuselage joints. Aircraft fuselage comprises circular joint between its sections, each comprising skin and stiffness element. Every said stiffness element is located opposite another stiffness element at joint level and comprises two walls and two bases. Said two walls and two bases make, along with aforesaid skin, a closed cross-section. Two opposed stiffness elements are jointed together by strap. Stiffness part and sais strap are made from composite material. Said strap is jointed only with one stiffness part and comprises two walls and two separate bases. Every said base comprise thrust surface in contact with the base of every stiffness element and is secured to stiffness elements by working fasteners arranged only at strap bases. Every stiffness element comprises head between two walls to define so-called omega-shape cross-section of stiffness part.
EFFECT: reduced weight of fuselage.
9 cl, 11 dwg
