The RD862 engine is intended for thrust creation and flight control of LV second stage along the active leg of trajectory in pitch, yaw
and roll channels.
- The engine operates under a sceme of fuel-reach generator gas after-combustion.
- The flight contol is effected through injection of the generator gas into the supersonic part of the chamber nozzle.
The one-chamber one-mode one-run pump-fed engine is designed under the scheme of fuel-reach generator gas after-combustion.
The thrust vector control in pitch/yaw channels is effected by a gas-dynamic method based on injection of the fuel-rich generator gas
into the supersonic part of the chamber nozzle. The roll control is provided by special small jet nozzles.
The turbine's working medium is a fuel-rich gas produced by the gas generator through combustion of main propellants. During the
startup the TPU's rotor is spinned-up by pyrostarter driving the starting turbine
The control units are activated by pyroactators.
The engine is provided by systems supporting combustion chamber pressure and mixture ratio.
| Vacuum thrust, kgf | 14544 |
| Vacuum specific impulse, s | 331 |
| Mass, kg | 192 |
| Absolute pressure in CC, kgf/cm2 | 135 |
| Absolute pressure at nozzle exit, kgf/cm2 | 0.09 |
| Mixture ratio | 2.55 |
| Thrust deviation from the nominal value, % | ±1.3 |
| Mixture ratio regulation range, % | ±5.5 |
Propellants
- oxidizer
- fuel |
NTO
UDMH |
Min absolute inlet pressure of propellants (at temperarture of 40°Ñ), kgf/cm2:
- oxidizer
- fuel |
4.45
2.0 |
| Max steering force in pitch or yaw planes, kgf | 300 |
| Max moment in roll channel, kgf x m | 15 |
| Burn time, s | 195 |
Development of company
