FIELD: aviation; heavier-than-air flying vehicles; designing passenger and transport aircraft.
SUBSTANCE: proposed aircraft has fore horizontal plane which is articulated on axle perpendicularly relative to plane of symmetry at derivative of lift force coefficient by angle of attack of Cαang≈0 self-setting at required angle of attack and at lift force coefficient lesser than lift force coefficient for cruising modes of flight. Fore horizontal plane is included in control mechanism in longitudinal channel and its halves are provided with tubular spars whose ends are articulated on axle in bearing units mounted in fuselage nose. Ends of tubular spars are connected by means of connecting pipe. Halves of horizontal plane are provided with servo-tabs in their tail portion which are provided with articulation rods connected with control mechanism of horizontal plane.
EFFECT: enhanced controllability of aircraft in longitudinal channel due to fore horizontal plane.
6 cl, 3 dwg
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