FIELD: engines and pumps.
SUBSTANCE: invention relates to solid-propellant rocket nozzleless engines. Claimed engine comprises the body and the rocket propellant grain with longitudinal channel. Said propellant grain has enclosed radial slit-like cavities. The ratio between the rocket propellant components is as follows: lithium aluminium hydride - 21.50 wt %, nitrogen pentoxide - 61.19 wt %, decaborane - 17.31or lithium aluminium hydride - 20-40 wt %, ammonia dinitroamide - 53.33 wt %, decaborane - 26.27 wt %.
EFFECT: higher grain gas capacity.
3 dwg
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RU2570012C1 |
