SOLID-PROPELLANT ROCKET ENGINE Russian patent published in 1999 - IPC

FIELD: rocketry. SUBSTANCE: rocket engine has charge armored over outer surface and mounted in combustion chamber at circular clearance and seal forming stagnant zone which is gas-dynamically communicated with combustion chamber. Cross-section area of circular clearance increases towards seal. Cross section area at circular clearance inlet ((F_in)) is found from relationship F_in>F_cr where F_cr is area of engine critical section. Construction of engine ensures avoidance of burn-out and carrying armor coat from charge. EFFECT: enhanced reliability and efficiency; reduced thickness of armor coat and heat insulation of inner surface of combustion chamber; reduced smoking at initial section of engine operation; increased coefficient of filling combustion chamber with charge. 1 dwg