METHOD FOR DAMPING OF OPERATING SOLID-PROPELLANT ROCKET ENGINE DURING TESTS, AND PLANT FOR ITS IMPLEMENTATION Russian patent published in 2013 - IPC F02K9/96 

FIELD: engines and pumps.

SUBSTANCE: when damping an operating rocket engine, a cooling agent is supplied to combustion chamber of the tested engine. First, cooling agent is supplied to a device ensuring its supply to combustion chamber at the end of the engine operation. Cooling agent is supplied to the above device in the time range from the rocket engine starting mode to the beginning of pressure drop when pressure level in rocket engine is higher than the specified pressure of supplied cooling agent to combustion chamber. Operating rocket engine damping plant includes a cooling agent source connected by means of a pipeline through a cutoff valve to the tested engine combustion chamber. A device is installed on the pipeline between the cutoff valve and the tested engine, provides cooling agent supply to combustion chamber and has such actuation pressure that corresponds to the rocket engine chamber pressure level required for damping. Pipeline is provided with a pressure gauge that is located between the cutoff valve and the device providing cooling agent supply to combustion chamber.

EFFECT: inventions allow improving reliability of the information on the state of material part after tests, as well as reducing the influence of a human factor on test results.

2 cl, 1 dwg