CONVERTIPLANE Russian patent published in 2025 - IPC B64C37/00 B64C27/28 

FIELD: aviation.

SUBSTANCE: invention relates to the field of aviation technology. The tiltrotor contains a fuselage, a control system, a power plant, aerodynamic wing consoles with aerodynamic control surfaces, front wings with aerodynamic control surfaces, a tail boom and propeller groups (VMG). The front VMG is located in nacelles with the possibility of rotation on the tips of the front wings. The statically positioned VMG is fixed to the tail boom. The tiltrotor is designed to ensure the coincidence of the aerodynamic center of pressure and the resulting thrust vector, as well as the possibility of their mutual dynamic and static scalar control due to the operation of aerodynamic control surfaces and thrust vector control each of the front VMG, made with an axial degree of freedom and with the possibility of independently controlling the change in thrust vector, speed and angle of installation of the blades. The VMG nacelles on the ends of the two front wings are equipped with additional statically fixed wings parallel to the axis of rotation of the propellers, while the center of pressure and the center of gravity of the tiltrotor are not tied to the intersection of the medians, they can move in the area of displacement of the resulting thrust vector with the center of pressure shifting backward relative to the center of gravity. The tail rotor has a smaller diameter than the front ones and a configurable tilt in the vertical plane "YZ" up to 20 degrees on both sides of the vertical axis "OY". Wing consoles with aerodynamic control surfaces on the tips are equipped with mixed-cut winglets.

EFFECT: due to these differences, the airframe's energy efficiency and flight stability in the convertoplane's transition modes are controlled.

7 cl, 3 dwg