FIELD: engines and pumps.
SUBSTANCE: invention relates to the field of rocket engines that operate on solid propellant, for instance, accelerating engines of controlled missiles or engines to separate stages of ballistic carrier rockets. A solid propellant rocket engine comprises a combustion chamber, an igniter, a powder grain, a reheat charge and a gas-dynamic stabiliser with a calibrated nozzle. The gas-dynamic stabiliser is installed between the reheat charge and the powder grain and is arranged in the form of two cartridge clips that embrace an elastic element. The first cartridge clip facing the reheat charge is fixed on the bottom of the combustion chamber, and the calibrated nozzle is placed into the second cartridge clip. The elastic element is arranged in the form of a conical spiral with ratio of the larger cone diameter to the smaller one equal to 1.6-2.7.
EFFECT: invention makes it possible to ensure stability of engine operation by elimination of high-frequency oscillations of pressure.
2 dwg
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RU2620613C1 |
| SOLID PROPELLANT ROCKET ENGINE | 1973 |
|
SU1840811A1 |
