The engine is intended for thrust creation and flight control in all control channels of LV upper stages.

- Thrust regulation system and system of mixture ratio maintenance with accuracy of ±1%;
- Total operational time in flight is no less than 1100s;
- High reliability is based on utilization of developed combustion chamber from the RD-8 engine;
- Scheme of generator gas afterburning.

The one-chamber multi-start pump-fed engine is designed under a scheme of generator gas afterburning.
The thrust vector control is realized through the chamber gimbaling in two orthogonal planes. The roll control is provided by respective roll nozzles.
The spinning-up of the booster turbopump and operation of solenoid valves is performed by gas from a pneumatic unit intended for these tasks and installed on the engine.
Working medium of the turbine is oxidizer-rich gas.
The propellants are ignited in the gas generator and combustion chamber under use of a starting fuel. The engine's startup is provided by the booster turbopump of oxidizer and autonomous ignition unit.