NOZZLE UNIT OF SOLID-PROPELLANT ROCKET ENGINE Russian patent published in 2004 - IPC

FIELD: rocket engines.

SUBSTANCE: proposed nozzle unit of solid-propellant rocket engine has divergent nozzle, movable center body, temperature controller and tube-retainer. Movable center body has three spaces of variable volume: front spring variable-pressure space, middle constant-pressure space, and rear low-pressure space. Front spring variable-pressure space is connected by channel and throttling hole with combustion chamber, and through exhaust ports, with exhaust channel. Exhaust ports are made in form of longitudinal slots overlapped by spool plunger from front edge and movable partition of center body from rear side. Middle constant-pressure space is connected by channel and throttling hole with combustion chamber, by channel with front variable-pressure space, and through pressure-relief valve, with rear low-pressure space. Rear low-pressure space is connected with constant-pressure space through pressure-relief valve, and with central exhaust channel through exhaust hole (port) in guide bushing providing equality of pressures in rear space and exhaust channel.

EFFECT: provision of quick action of thrust stabilization system by decreasing mass of movable parts and reducing volumes of working spaces.

1 dwg