 RD-859 engine was used as a backup one in composition
of the engine cluster intended for provision of a soft landing onto the Moon surface, liftoff from the Moon surface and injection of the
Lunar vehicle into an elliptic orbit of artificial satellite of the Moon.
- High reliability of the engine, confirmed by autonomous tests including operation in an orbit.
- Possibility of a repeated startup after only three seconds since a shutdown.
The autonomous two-chamber one-mode engine of double startup with thrust regulation and pump delivery of hypergole propellants is
designed in accordance with an open generator scheme.
The turbine's working medium is a gas produced by the gas generator through combustion of the main propellants. During a startup the TPU
rotor is spinned-up by pyrostarter.
The inlet valves are opened during a startup by gas from a manifold of the pyrostarter.
Control of the valves operation is effected by fuel pressure taken from the pump outlet.
The engine's shutdown is provided by the control system through pyrovalves.
The engine has systems of thrust tregulation and mixture ratio maintenace.
| Vacuum thrust (with TPU exhaust nozzles thrust), kgf | 2045 |
| Thrust regulation range, % | ±9.8 |
| Vacuum specific impulse, s | 312 |
| Mass, kg | 57 |
| Combustion chamber absolute pressure, kgf/cm2 | 80 |
| Absolute pressure at nozzle exit, kgf/cm2 | 0.07 |
| Mixture raito | 2.0 |
| Mixture ratio deviation from the nomial value, % | 3 |
Propellants:
- oxidizer
- fuel |
NTO
UDMH |
Minimum absolute inlet pressure of propellants at tempearture of +35°Ñ, kgf/cm2:
- oxidizer
- fuel |
3.6
1.5 |
Total burn time, s
including:
- during the first run
- during the second run |
up to 400
3
up to 400 |
|
Development of company
