FIELD: aviation.
SUBSTANCE: invention relates to aeronautical engineering, in particular to rotor support structures. Main rotor with folding retractable blades comprises the main reducer shaft, to the upper end of which a horizontally located main rotor hub with lugs equal in number to the number of blades is attached. In each lug, there is a vertical hinge to which an axial hinge is attached, to which, in turn, a drum with an inner coil is attached, to which the base part of an elastic blade is attached. Blades of the main rotor have a convex-concave profile, allowing compact, deformation-free and breakage-free synchronous folding and unfolding of the blades around the coils of the drums using the system of controlled retraction and release of the blades. To the other end of each blade, a centrifugal load with a stabilizer with a controlled servo is attached.
EFFECT: size and weight of the main rotor are reduced, the efficiency of the main rotor is increased, its efficiency and controllability are improved.
8 cl, 18 dwg
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