FIELD: aircraft engineering.
SUBSTANCE: invention relates to structural system for aircraft. Technical result is achieved by structural system for aircraft, which comprises elongated composite element (302) having first side (334) fixed on the structure (306) and second side (331), which is opposite to the first side (334). Channel (332) on the first side extending along the length of elongated composite element (302). Plurality of composite structures (304), arranged in the channel to secure elongated composite element side section on the structure (306), wherein number of composite structures (304) increases capacity of elongated composite element (302) to resist to forces, which pull elongated composite element (302) out of structure (306). Where structural system comprises the third structure. Elongated composite element (302) is a side girder, structure (306) represents an outer skin panel attached to the first side (334) of side girder, and the third structure represents a rib attached to the second side (331) of side girder.
EFFECT: technical result is higher strength of structural system for aircraft without increase of weight and complexity of manufacturing.
7 cl, 20 dwg
