SOLID-PROPELLANT ROCKET ENGINE Russian patent published in 1998 - IPC

Abstract RU 2111372 C1

FIELD: starting propulsion engine of projectiles and missiles after expelling from barrel or container. SUBSTANCE: engine has housing 1, insert charge 3 with open end surface 4 and igniter 5. Circular cavity 4 is formed between change 3 and inner surface 6 of housing. Nozzle support has through radial slots 8 on side of change. Circular chamber is gas-dynamically connected with igniter zone 9 through slots 8. EFFECT: enhanced reliability of rocket engine in course of ignition of change and attaining the mode. 2 dwg

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RU 2 111 372 C1

Authors

Mironov Ju.I.

Berkovich V.S.

Kolotilin V.I.

Shigin A.V.

Dates

1998-05-20Published

1995-03-28Filed