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 |
| 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 | |
