FIELD: transport.
SUBSTANCE: invention relates to rocketry. proposed power plant comprises oxidiser tank and propellant tank to feed propellant to sustainer engine, high-pressure cylinder, pressure reducer with its drain union communicated by feed line with high-pressure cylinder. Power pant incorporates, additionally, pyro valve with two outlets and check valve. Pyro valve inlet is communicated with pressure reducer drain union. Pyro valve first inlet is provided with inner chamber protection element with discharge union. Pyro valve second outlet is communicated via check valve with fuel-tank pressurisation pipeline.
EFFECT: higher reliability in air tests and preparation for launching.
2 dwg
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