FIELD: aviation.
SUBSTANCE: invention relates to the field of aviation, in particular to structures of composite blades of rotary-wing aircrafts. Rotor (3, 5) contains sleeve (6, 8), a group of blades (7, 14). Each blade (7, 14) contains front edge (20) and rear edge (21), upper surface (22) and lower surface (23), closed shell (30). Shell (30) contains first and second elements (31, 32) separate from each other, limiting corresponding shell (30) from mutually opposite sides, first connecting element (34) located on a side of related front edge (20) and placed between first ends (37, 38) of corresponding first and second elements (31, 32); and third element (80) connected to related first and second elements (31, 32) and located on a side of front edge (20). Blade (7, 14) contains fourth element (70) placed between third element (80) and first connecting element (34).
EFFECT: reduction in a number of blade components, high axial rigidity, and bending stiffness in a drag plane of a blade.
13 cl, 5 dwg
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