SOLID-PROPELLANT ROCKET ENGINE

rocketry; manufacture of restartable engines with thrust cut-off. SUBSTANCE: engine includes casing, nozzle, charge, ignition devices and quenching unit consisting of sleeve with differential piston dividing this sleeve into above-piston and under-piston cavities; it is fixed with lock; under-piston...

Ausführliche Beschreibung

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Bibliographische Detailangaben
Hauptverfasser:	SHLJAPIN JA.K, TODOSHCHENKO A.I, NALOBIN M.A, IOFFE E.I, SOKOLOVSKIJ M.I, OGNEV S.V, LJANGUZOV S.V
Format:	Patent
Sprache:	eng
Schlagworte:	BLASTING COMBUSTION ENGINES HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS JET-PROPULSION PLANTS LIGHTING MECHANICAL ENGINEERING WEAPONS
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Beschreibung
Zusammenfassung:	rocketry; manufacture of restartable engines with thrust cut-off. SUBSTANCE: engine includes casing, nozzle, charge, ignition devices and quenching unit consisting of sleeve with differential piston dividing this sleeve into above-piston and under-piston cavities; it is fixed with lock; under-piston cavity of sleeve contains working fluid. Side cylindrical surface of sleeve is provided with ports on side of above-piston cavity; under-piston cavity of sleeve has drain hole made in differential piston or in sleeve. Engine is provided with receiver connected with drain hole. Receiver is connected with gas duct of nozzle through check valve. Receiver is made in differential piston. Under-piston cavity is provided with baffle plate mounted on sleeve (or on differential piston) which forms hydraulic brake together with drain hole. EFFECT: improved power and mass characteristics of engine due to reduction of its mass. 5 cl, 2 dwg