FIELD: transport.
SUBSTANCE: invention relates to aircraft engineering, particularly, to aircraft control systems. Control method for aircraft (1) containing fuselage (2), lifting propeller (3), variable-pitch thrust propeller (4), two half-wings (11, 11') located on both sides of fuselage (2), horizontal stabiliser (20) equipped with moving surface (21, 21'), power plant (5) rotating lifting propeller (3) and thrust propeller (4) includes determination of specified collective pitch and specified longitudinal cyclic pitch to bring the mentioned aircraft (1) to point of optimised operation of the mentioned lifting propeller (3) during stable phase of flight while keeping task of constant vertical state, such as constant vertical speed or constant angle of attack, and task of constant longitudinal spatial position corresponding to the mentioned stable phase of flight. Lifting force of the mentioned half-wings (11, 11') is regulated by acting on aerodynamic facility of the mentioned aircraft (1) so that collective pitch of the mentioned blades of the mentioned lifting propeller (3) could be equal to specified collective pitch.
EFFECT: lowering pilot functional stress due to automatic maintaining of aircraft spatial position.
12 cl, 5 dwg
