FIELD: flying vehicles of vertical takeoff and landing.
SUBSTANCE: proposed rotoroplane has fuselage located between two rotors with wings whose longitudinal axes are located in horizontal planes, wing angle-of-attack control mechanism and engine. Each wing consists of separate thin-profile blades; the profile is symmetrical relative to chord; blades are mounted at spaced relation and are connected into integral wing by means of ribs on which semi-axles are mounted; these axles are received by holes in struts rigidly connected with rotor shaft. Reflecting board-wing is mounted after each rotor in parallel with axis of its shaft on framework secured on tail boom; this board-wing is directed to rotor whose section is made from deformable material. Wing angle-of-attack control mechanism has hub with rings mounted on cylindrical surface of its free end; these rings are connected with tenon on rib of each wing by means of rod. Other part of hub is located in ports of vertical and horizontal slide blocks moved simultaneously with hub relative to axis of shaft of rotor passing inside this hub. End part of rotor shaft is provided with ring for elimination of action of gravity load; this ring is rigidly connected with strut on tubular part of rotor shaft; its cylindrical surface is received by grooves secured on fuselage.
EFFECT: improved aerodynamic properties of wing; possibility of forming additional lifting force; enhanced reliability of control mechanism.
3 cl, 10 dwg
