FIELD: rocket technology.
SUBSTANCE: invention relates to rocket technology and is intended for use in multiple rocket launch systems. The rocket part contains a combustion chamber with a body and bottom, a nozzle and a damper for damping acoustic vibrations. The damper is made in the form of longitudinally arranged, interconnected ribs made of heat-resistant material placed at the bottom of the combustion chamber. The length of the damper is (0.15…0.30)D. A ring with a difference of external and internal radius (0.20…0.35)D is placed on the end surface of the damper facing the nozzle. The damper and the ring are made of composite materials with a high absorption capacity of acoustic vibrations. The bottom is provided with an axial cylindrical protrusion adjacent to the body of the combustion chamber, with a width of (0.2…0.5)D and an internal diameter of (0.90…0.97)D, where D is the internal diameter of the body.
EFFECT: invention makes it possible to increase reliability of the functioning of the rocket part.
1 cl, 1 dwg
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