FIELD: rocketry.
SUBSTANCE: proposed solid-propellant rocket engine consists of combustion chamber with nozzle unit, powder charge, igniter and electric igniter. High-pressure chamber in head part of engine is formed by circular cavity in engine housing and perforated disk. Holes in perforated disk open into radial cavities made in disk from side of powder charge. Igniter is made in form of weighted amount of powder placed in sealed case made of combustion material and is arranged inside high-pressure chamber. Electric igniter is installed at angle to longitudinal axis of engine. Longitudinal axis of electric igniter lies in one plane with row of holes of perforated disk and rail cavity.
EFFECT: provision of reliable and uniform ignition of charge at reduced spread of characteristics within wide temperature range, improved reliability of engine.
3 cl, 3 dwg
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