RD-180
Glavkosmos
Liquid rocket engine with afterburning of oxidizing gas. Fuel: oxygen + kerosene. Winner of the competition for the development and supply of the engine for the first stage for the PH of the Atlas family of the American company ULA. More than 260 tests were carried out with a total operating time of
Technical specifications
- Thrust, earth / void, tf
- 390/423
- Specific impulse, earth / void, s
- 311 / 339
- Pressure in the combustion chamber, kgf / cm2
- 261.7
- Weight, dry / dipped, kg
- 5480/5950
- Dimensions height / diameter, mm
- 3600 / 3200
- Development period
- 1994-1999
- Thrust vector control by swinging cameras in the same plane, o
- 8
- Thrust range,%
- 100-47
About
Liquid rocket engine with afterburning of oxidizing gas. Fuel: oxygen + kerosene. Winner of the competition for the development and supply of the engine for the first stage for the PH of the Atlas family of the American company ULA. More than 260 tests were carried out with a total operating time of more than 50,000 s. Certified for 10 modifications of the Atlas launch vehicle. Engine operating time in 86 flights is more than 20,000 s. (01.09.2019).
Documentation
No public datasheet yet — request the datasheet / ICD from the supplier.
