SOLID-PROPELLANT ROCKET ENGINE Russian patent published in 2008 - IPC F02K9/18 

Abstract RU 2317433 C1

FIELD: rocketry.

SUBSTANCE: proposed solid-propellant rocket engine contains nozzle unit, igniter and solid-propellant charge with star-shaped section central channel and overhung nonrestricted rear end face rigidly connected with body. Channel of charge is provided with local conical widening from side of rear end face whose base coincides with plane limiting the charge. Length of conical section is 1.5-2.2 of length of charge overhung part. Diameter of base of conical section is 1.8-2.2 of channel diameter. Clearance equal to 0.1-0.2 of length of overhung part of charge from side of rear end face is provided between end face of charge and nozzle bottom.

EFFECT: increased reliability of solid propellant rocket engine by reduction and thrust peaks at high rate of filling owing to choice of optimum relation of main design parameters.

4 dwg

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Authors

Kutsenko Gennadij Vasil'Evich

Kolesnikov Vitalij Ivanovich

Amarantov Georgij Nikolaevich

Shamraev Viktor Jakovlevich

Lazebnyj Valerij Nikolaevich

Dmitriev Anatolij Fedorovich

Guseva Galina Nikolaevna

Kuz'Mitskij Gennadij Ehduardovich

Vronskij Nikolaj Mikhajlovich

Makarov Leonid Borisovich

Zazhigin Aleksandr Evgen'Evich

Dudchak Vladimir Vlas'Evich

Gramenitskij Mikhail Dmitrievich

Volkov Oleg Kuprijanovich

Rats Viktor Antonovich

Bogatskij Vladimir Grigor'Evich

Levishchev Oleg Nikolaevich

Afonin Viktor Nikolaevich

Dates

2008-02-20Published

2006-06-29Filed