FIELD: rocket equipment.
SUBSTANCE: invention relates to the tests of thrusters. Device for altitude tests of rocket engines is comprises an after diffuser to allow continuous flow of combustion products in a rocket engine nozzle during tests and comprises two vacuum chambers and two vacuum gates. During the rocket engine operation, the after diffuser gas-dynamically disconnects the vacuum chambers, providing initial conditions in the first vacuum chamber. Vacuum chamber, into which combustion products enter through the diffuser, is connected to a system of vacuum pumps, maintaining negative pressure in it, which is necessary for continuous operation of the diffuser and non-continuous flow of combustion products in the engine nozzle, including with increased geometric degree of expansion.
EFFECT: invention allows to determine the main parameters of the thruster, as well as the parameters of the environment in which the tests are carried out.
3 cl, 1 dwg
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