SOLID-FUEL JET ENGINE NOZZLE

FIELD: rocket engineering; solid-fuel jet engines; launching rocket projectiles from tubular guides including those of salvo systems. ^ SUBSTANCE: proposed solid-fuel jet engine nozzle has subsonic part, supersonic part, insert in critical section of nozzle, and annular bench made of burning materia...

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Bibliographische Detailangaben
Hauptverfasser:	UGLOV VALERIJ MIKHAJLOVICH, SLEMZIN VALENTIN KONSTANTINOVICH, KOROLEVA NATAL'JA BORISOVNA, DENEZHKIN GENNADIJ ALEKSEEVICH, DRUZHININ VLADIMIR GEORGIEVICH, PETURKIN DMITRIJ MIKHAJLOVICH, TARASOV ANATOLIJ IGNAT'EVICH, MAKAROVETS NIKOLAJ ALEKSANDROVICH, KASHIRKIN ALEKSANDR ALEKSANDROVICH, SEMILET VIKTOR VASIL'EVICH, TREGUBOV 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: rocket engineering; solid-fuel jet engines; launching rocket projectiles from tubular guides including those of salvo systems. ^ SUBSTANCE: proposed solid-fuel jet engine nozzle has subsonic part, supersonic part, insert in critical section of nozzle, and annular bench made of burning material. Annular bench is made in the form of axially symmetric bushing disposed on supersonic part of nozzle and spaced from its critical section through distance equal to 0.1 - 0.3 of nozzle critical section diameter. Minimal inner diameter of bushing equals 0.85 - 0.98 of nozzle diameter at installation point of annular bench. Butt-end surface of bushing facing critical section of nozzle has cylindrical section and section perpendicular to nozzle axis. ^ EFFECT: reduced impact of condensed phase in combustion products on rocket projectile guide. ^ 1 cl, 1 dwg