The RD810 generates thrust and controls flight of launch vehicle first stages. The staged-combustion engine is based on proven Zenit launch vehicle technologies. The RD810 is a single-chamber, dual-mode single-burn engine with a turbo-pump-feed system.
The engine gimbaling in two mutually perpendicular planes provides thrust vector control. A starting fuel is used to ignite propellants in the chamber and the gas generator.
The turbopump assembly turbine uses oxygen-rich gas as a working fluid. The RD810 engine can be used for development of an 800-ton-thrust engine cluster incorporating four RD810 engines. The engine is currently in development.
Basic Specifications
|
Engine mass, kg, not more than |
2800 |
|
Propellants: Oxidizer Fuel |
Liquid oxygen Kerosene |
|
Thrust, kgf: Sea-level Vacuum |
191314 214639 |
|
Vacuum specific impulse, kgf·s/kg: Sea-level Vacuum |
299 335,5 |
|
Propellant mixture ratio |
2,65 |
|
Gimbal angle, ang.deg |
±8 |
|
Running time in flight, s |
Up to 300 |
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