FIELD: engines and pumps.
SUBSTANCE: two-mode solid propellant rocket engine comprises cylindrical housing, launch and sustainer combustion chambers with gunpowder channel-type charges, separating bottom, bottom opening device and nozzle. Bottom opening device represents spherical perforated plugs arranged in symmetry about engine lengthwise axis on separating bottom, protruding towards sustainer chamber. On the side of sustainer chamber, said plug interacts with thin-wall membrane mating the plug shape and tightly secured along plug edges and furnished with heat-protection coating. Said plug is arranged opposite sustainer gunpowder channel. Perforation size is selected proceeding from relationships protected by this invention.
EFFECT: higher reliability.
4 dwg
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