CONTROLLED SOLID PROPELLANT ROCKET ENGINE Russian patent published in 2010 - IPC F02K9/86 

FIELD: engines and pumps.

SUBSTANCE: invention relates to rocketry and can be used in developing solid propellant engines with controlled thrust. Proposed engine comprises housing, nozzle with actuating element arranged to move axially relative to nozzle in its taper gas path, and control drive. Actuating element diametre equals nozzle gas path minimum diametre to form cylindrical surface of nozzle minimum low section there between. Aforesaid taper part of gas path represents a plate-like nozzle. Prismatic ledges are arranged along the circumference of the actuating element end face. Outer surface of said elements is aligned with actuating element cylindrical surface and contacts the nozzle on its gas path minimum diametre section.

EFFECT: full closing of nozzle and linear dependence of flow arte upon actuating element stroke, reduced nozzle length and engine sizes, simple design and higher reliability.

3 cl, 3 dwg