SOLID-PROPELLANT ROCKET ENGINE

SOLID-PROPELLANT ROCKET ENGINE

FIELD: rocketry. ^ SUBSTANCE: invention can be used in designing solid-propellant rocket engines with high propellant loading ratio, particularly, with blind channel. Proposed solid-propellant rocket engine has charge with central channel connected with body and burning end face, nozzle assembly and...

Ausführliche Beschreibung

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Bibliographische Detailangaben
Hauptverfasser: SOKOLOVSKIJ MIKHAIL IVANOVICH, KARIMOV VLADISLAV ZAKIROVICH, KREMLEV ALEKSEJ NIKOLAEVICH, IOFFE EFIM ISAAKOVICH, NAZAROV ANATOLIJ ALEKSEEVICH, SARAB'EV VIKTOR IVANOVICH
Format: Patent
Sprache:eng ; rus
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:FIELD: rocketry. ^ SUBSTANCE: invention can be used in designing solid-propellant rocket engines with high propellant loading ratio, particularly, with blind channel. Proposed solid-propellant rocket engine has charge with central channel connected with body and burning end face, nozzle assembly and igniter. The latter is arranged in zone of mating of burning end face and channel of charge. Ignition consists of housing in form of tubular ring with perforation filled up with pyrotechnical compound. Perforation is made in form of holes arranged over circumference with axis common with axis of engine and pointed inside charge channel, and holes pointed to zone of mating of burning end face and change channel. ^ EFFECT: improved energy producing characteristics and provision of quick and stable coming to conditions with high propellant loading ratio owing to simultaneous ignition of charge over entire burning surface. ^ 3 cl, 5 dwg