FIELD: aircraft engineering.
SUBSTANCE: proposed method consists in determination of rotor thrust components for killing of forward speed starting from 75-60 km/h. Horizontal and vertical speed are measured by the system of appropriate meters and helicopter landing path is defined. Swash plate deflection in lengthwise direction is defined as well as rotor approach to vortex ring" zone is signalled at helicopter pre-landing manoeuvres at deceleration conditions. At deceleration, dead drag is increased by increasing the helicopter glide angle to the right to 60-65 degrees (RH turn) or dead drag is increased by smooth increase at deceleration to magnitude equal to at least 65 degrees by release of brake flaps of blower thrust, said blowers being arranged at joint between fuselage and tail boom above the centre of gravity of helicopter.
EFFECT: decreased dynamic loads, longer life of blades.
2 cl, 4 dwg
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