GUIDED MISSILE SOLID-PROPELLANT ROCKET ENGINE, SOLID PROPELLANT IGNITER AND ROCKET ENGINE NOZZLE ASSEMBLY

FIELD: engines and pumps. ^ SUBSTANCE: proposed rocket engine comprises a housing with the powder gas cleaning unit, igniter, solid propellant inserted charge, axial pipe arranged in the charge central channel, nozzle plug and additional powder gas cleaning device representing composite two-layer pipe arranged in the gap formed between the engine housing inner wall and the powder charge outer surface the pipe inner layer length is smaller than that of the outer layer and makes a gap with O-ring. The inserted charge face load-bearing surface, on the side of the barrel axial overload, is formed by the combination of armored and open concentric rings. A torus-shaped recess is made in the housing opposite the nozzles. Axial pipe is arranged in the engine housing elements to move therein. This invention covers also the igniter of the above described charge comprising torus-shaped afterburner with outlets filled with the igniting powder tablets, initiating compound, igniting powder tablets with through holes adjoining the initiating compound and thermal-stability plastic imitators. The afterburner outlet holes are directed towards and at an acute angle to non-armored surface of the powder charge end face. The inlet of these holes is arranged in blunt conical space formed by the tapered recess on the afterburner cover on the axial side. The invention covers also the rocket engine nozzle assembly comprising nozzles in truncated pyramidal ledges fitted into the engine front part housing, and nozzle plugs representing fungus with a foot, spherical head and rubber seal ring in contact with the nozzle outlet funnel. The said foot features symmetrical flat lateral surfaces changing over into a collet collar pressed against the nozzle outlet surface by threaded joint between the fungus foot and head. ^ EFFECT: transparent rocket engine exhaust gases during ignition and stable operation, higher reliability of powder charge ignition. ^ 3 cl, 5 dwg Ракетный двигатель твердого топлива управляемого снаряда содержит корпус с узлом очистки пороховых газов, воспламенитель, вкладной заряд твердого топлива, осевую трубку, размещенную в центральном канале заряда, сопловую заглушку и дополнительный узел очистки пороховых газов. Дополнительный узел очистки пороховых газов выполнен в виде составной двухслойной эластичной трубы, размещенной в зазоре, образованном между внутренней стенкой корпуса двигателя и наружной поверхностью порохового заряда. Внутренний слой трубы выполнен по дли