ABOUT RD-180
The RD-180 is a dual-chamber, dual-nozzle oxygen-rich staged combustion engine developed by NPO Energomash in Russia. It powered the first stage of the Atlas V launch vehicle and was acclaimed for its high performance and reliability. The engine is derived from the RD-170 design, essentially using half of that engine’s four-chamber configuration.
Image: ULA
PERFORMANCE
| Thrust (Sea Level) | 3,827 kN (860,200 lbf) kN |
| Thrust (Vacuum) | 4,152 kN (933,400 lbf) kN |
| ISP (Sea Level) | 311 s s |
| ISP (Vacuum) | 338 s s |
| Chamber Pressure | 26.7 MPa (3,870 psi) bar |
| Mass | 5 kg |
| Thrust-to-Weight | 78 |
| Throttle Range | 47–100% |
| Restart Capable | No |
THRUST CONVERSIONS (VACUUM)
| Kilonewtons | 4.0 kN |
| Pounds-force | 899 lbf |
ENGINE CYCLE
Oxygen-Rich Staged Combustion
PROPULSION
| Propellant | RP-1 |
| Oxidizer | LOX |
| Engine Cycle | Oxygen-Rich Staged Combustion |
| Mixture Ratio | 2.72:1 |
| Flow Rate | ~1,250 kg/s kg/s |
PHYSICAL
| Dimensions | 3.15 m diameter × 3.56 m length |
| Combustion Chambers | 2 |
| Nozzle Expansion Ratio | 36.87:1:1 |
GENERAL
| Manufacturer | NPO Energomash |
| Country | Russia |
| Status | Active (limited stock) |
| First Flight | April 22, 2026 |
VARIANTS (1)
- RD-180
VEHICLES USING RD-180 (2)
- Atlas III
- Atlas V
ENGINE LINEAGE
⚖ PROPELLANTS
