SOLID-PROPELLANT ROCKET ENGINE Russian patent published in 2004 - IPC

FIELD: rocketry.

SUBSTANCE: proposed solid-propellant rocket engine has combustion chamber with nozzle unit and solid-propellant charge arranged in combustion chamber. Housing of combustion chamber is made conical, with cylindrical section from side of nozzle unit and transition conical section at front bottom mated by radius with main conical section of housing. Solid-propellant charge is attached to combustion chamber walls. Cylindrically conical space is made in form part of solid-propellant charge terminating in cylindrical neck with cross-section area smaller than summary critical section area of nozzle unit. Inner surface of charge channel after neck is made conical, widening in direction of rear end face. Ball is made at rear end face in charge channel terminating in cylindrical section with diameter exceeding diameter f critical section of nozzle unit.

EFFECT: reduced dust and smoke interferences, increased power characteristics of engine.

2 cl, 3 dwg