FIELD: astronautics.
SUBSTANCE: invention relates to rocketry, namely to stand equipment used in fire bench tests of solid propellant rocket engines. Plant for damping solid propellant rocket engine during tests contains connected with coolant feed system hollow bar with a nozzle. Between the hollow rod with Injector and coolant feed system are telescopically coupled to each other hollow pistons, wherein in each piston skirt manifold coolant flow, and in the bottom of each piston has radial channels connecting the cavity of the piston in its extended position to collector of the coolant flow adjacent piston. Along the perimeter of headers of cooling liquid flow nozzles. On the hollow piston is installed centering mechanism made in the form of rods with retainers initial and final positions.
EFFECT: invention enables to obtain reliable information on the State of material part, including elongated rocket engines, as well as high-altitude rocket engines at firing bench tests in gas-dynamic pipes.
2 cl, 9 dwg
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