ADJUSTABLE SOLID-PROPELLANT ROCKET ENGINE Russian patent published in 2012 - IPC F02K9/92 F02K9/86 

FIELD: engines and pumps.

SUBSTANCE: proposed engine comprises combustion chamber with igniter arranged at its bottom, injector, thrust control device and hydraulic damper assembly. Combustion chamber houses solid-propellant charge and pressure pickup mounted therein and connected with feedback pickup and onboard computer. Thrust control assembly comprises actuator with rod to accommodate motion transducer. Hydraulic damper assembly comprises injector, flow rate meter, solenoid valve arranged in fuel pressure line, air-charged accumulator and fluid coolant pressure pickup. Solid-propellant charge has channels filled with coolant forced by pistons and communicated with flow dividers. Hydraulic damper assembly and combustion chamber are communicated via extra branch pipe and second controlled flow rate meter.

EFFECT: improved control over thrust vector.

1 dwg