FIELD: aerospace engineering, engines and pumps.
SUBSTANCE: invention relates to ascent solid propellant engines wherein power conversion period is limited by second hundredth and thousandth. Proposed engine comprises shell and engine gasdynamic section comprising central perforated tube with bundle of solid propellant disk-type elements arranged thereabout and in perforated combustion chamber, igniter and outer flow annular nozzle. Combustion chamber features cylindrical casing with inclined tangential slots with flow section area decreasing along combustion chamber length from section to section. Solid propellant disk-type elements feature equal size and integrated into a charge with the help of powder supports glued onto their face surfaces. Powder supports feature burning hill thickness equal to half the thickness of disk-type element burning hill.
EFFECT: more complete combustion of powder charges, increased specific thrust pulse.
2 dwg
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