| 摘要 |
FIELD: aircraft engineering. ^ SUBSTANCE: proposed method comprises varying rotor-blade angle to produce maximum difference in said angles in first half of rotor revolution in between 60 and 120, as related to those in between 240 and 300 in second half of rotor revolution, to rule out stall and to control direction and thrust produced by rotor blades in flight at low speeds and at those notably exceeding helicopter speeds. Proposed method allows producing thrust vector in preset maneuver direction and increasing lift on braking by rotors. ^ EFFECT: increased lift, with no reversing zones, and use of blade angles of attack approximating to feathering angles on larger part of blade revolution. ^ 38 cl, 37 dwg |
