FIELD: engines and pumps.
SUBSTANCE: plant for damping an operating solid-propellant rocket engine when being tested in a gas-dynamic pipe includes a cooling agent source and a device for cooling agent supply to a combustion chamber, which is connected to it through a control valve. An injector is arranged in the gas-dynamic pipe after the nozzle section, and in front of the injector there installed are atomisers connected to the cooling agent source through the control valve that is actuated when the specified pressure is achieved in the combustion chamber. The device for supply of the cooling agent to the combustion chamber is provided with an opening element made in the form of a cylinder inside which a hollow piston with a conical stock is arranged. In the stock there are cooling agent supply channels, and a pyro cartridge is installed on the cylinder body.
EFFECT: invention allows reducing the time for damping the solid-propellant rocket engine when being tested in a gas-dynamic pipe.
2 dwg
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