Description

The RD-815 generates thrust and controls flight of launch vehicle first stages.The RD810 is a single-chamber, dual-mode single-burn engine with a turbo-pump-feed system, as propellants used kerosene and liquid oxygen with a ratio of 2.7.

Specifications

Thrust, kgf:

Sea-level

Vacuum

 

251,3

274,5

Vacuum specific impulse, kgf·s/kg:

Sea-level

Vacuum

 

306,7

335

The pressure in the combustion chamber, kgf/сm2 200
The ratio of fuel components 2,7
Enginemass, kg 3 200
Note: These are preliminary characteristics of the engine