METHOD OF ATMOSPHERIC AIR EJECTION TO INCREASE THRUST OF CRUISE PROPULSION SYSTEM OF CARRIER ROCKET AND LAYOUT OF PIN NOZZLE UNIT FOR IMPLEMENTATION THEREOF

FIELD: rocket equipment.SUBSTANCE: proposed invention relates to rocket engineering, and more specifically to jet engines, mainly to liquid-propellant rocket engines (LPE). Method of atmospheric air ejection to increase thrust of cruise propulsion system of carrier rocket includes creation of external ejecting gas flow from primary shortened Laval nozzles of multi-chamber propulsion unit with a shortened round central body at the first stage of carrier rocket and internal ejecting gas flow into annular mixing chamber in inner cavity of central body. Supply of internal ejecting supersonic gas flow is performed from primary shortened nozzles of propulsion system of second stage of carrier rocket, axis of symmetry of which coincides with axis of symmetry of shortened central body, and the lower edge of the primary shortened nozzles of the propulsion unit is aligned with the inlet portion of air intakes in the inter-tank space at the upper edge of the shortened central body. Assembly of pin nozzle assembly for method implementation includes primary shortened Laval nozzles with shortened central body in tail part of first stage of carrier rocket and primary shortened Laval nozzles of propulsion system of second stage of carrier rocket with shortened central body, which is embedded into inner cavity of shortened central body of first stage of carrier rocket, axis of symmetry of which coincides with axis of symmetry of shortened central body. Lower edge of primary shortened nozzles of propulsion system of second stage of carrier rocket is combined with inlet section of air intakes in intertank space at upper edge of shortened central body at a distance from outlet section of mixing chamber, which makes size, equal to L shortened to 30 % of primary full length of profiled central body, where L ≥ 1.4 Dout, and Dout - outlet section diameter of the mixing chamber at the bottom of the shortened central body.EFFECT: invention allows increasing thrust of cruise propulsion unit (PU) of carrier rocket (CR), increasing specific impulse of thrust of multi-chamber PU with LPE of first and second stages of CR of two-stage CR with parallel arrangement of stages.4 cl, 8 dwg Предлагаемое изобретение относится к ракетной технике, а более конкретно к реактивным двигателям, в основном к жидкостным ракетным двигателям (ЖРД). Изобретение позволяет увеличить тягу маршевой двигательной установки (ДУ) ракеты-носителя (РН), повысить удельный импульс тяги многокамерной ДУ с ЖРД первой и