The RD863 engine is intended for thrust creation and
flight control of LV first stage along the active leg of trajectory . The thrust vector control is effected by gimballing each combustion
chamber in one tangential plane.
- Design simplicity and high reliability.
- High power characteristics combined with moderate mass of the combustion chamber having nozzle of the tube structure.
The four-chamber one-run pump-fed engine with hypergolic propellants is designed under the generator scheme providing:
- fuel tank pressurization with fuel-rich gas;
- delivery of oxidizer and fuel into device for oxidizer tank pressurization and systems of preliminary pressurization of the second
stage tanks.
- delivery of working medium (fuel) into a system of hydraulic actuators.
The turbine's working medium is a gas produced by the gas generator through combustion of main propellants. During the startup
the TPU's rotor is spinned-up by pyrostarter
The pyrovalves are activated by pyrodrives under control system commands.
The engine maintains the specified thrust level.
| Sea level thrust, kgf | 28230 |
Specific impulse, s:
- at sea level
- in vacuum |
259
301 |
| Mass, kg | 310 |
| Absolute pressure in CC, kgf/cm2 | 90.5 |
| Absolute pressure at nozzle exit, kgf/cm2 | 0.46 |
| Mixture ratio | 2.15 |
| Thrust deviation from the nominal value, % | ±3 |
| Mixture ratio regulation range, % | ±4.7 |
Propellants
- oxidizer
- fuel |
NTO
UDMH |
Min absolute inlet pressure of propellants (at temperarture of 47°Ñ), kgf/cm2:
- oxidizer
- fuel |
4.2
2.2 |
| Chamber gimbal angle, deg | ±38 |
| Burn time, s | 130 |
Development of company
