FIELD: aviation.
SUBSTANCE: invention relates to the structures of combined rotary-wing aircrafts. The combined aircraft (1) comprises a body (2), a rotary wing (3), main moment compensation device (4) and two wings (11, 11') located on one side and the other side of the mentioned body (2). Each wing (11, 11') comprises at least one movable flap (12, 12') located at the level of its rear edge. The mentioned flaps (12, 12') can be asymmetrically oriented with respect to the air flow formed as a response to the aerodynamic lift of the mentioned rotary wing (3) on one side and the other side of the mentioned body (2) to create longitudinal aerodynamic forces of the opposite direction on one side and the other side of the mentioned body (2).
EFFECT: possibility of creating additional rotation moment.
16 cl, 6 dwg
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