Centaur (rocket stage)
A single-engine Centaur III being raised for mating to an Atlas V rocket | |
| Manufacturer | United Launch Alliance |
|---|---|
| Used on |
|
| Associated stages | |
| Derivatives | Advanced Cryogenic Evolved Stage (cancelled, not flown) |
| Launch history | |
| Status | Active |
| Total launches | 273 as of October 2024 |
| Successes (stage only) | 254 |
| Failed | 15 |
| Lower stage failed | 4 |
| First flight | May 9, 1962 |
| Centaur III | |
| Height | 12.68 m (499 in) |
| Diameter | 3.05 m (120 in) |
| Empty mass | 2,247 kg (4,954 lb), single engine 2,462 kg (5,428 lb), dual engine |
| Propellant mass | 20,830 kg (45,920 lb) |
| Powered by | 1 × RL10A, 2 × RL10A or 1 × RL10C |
| Maximum thrust | 99.2 kN (22,300 lbf), per engine |
| Specific impulse | 450.5 seconds (4.418 km/s) |
| Burn time | 904 seconds |
| Propellant | LOX / LH2 |
| Centaur V | |
| Height | 12.6 m (41 ft) |
| Diameter | 5.4 m (18 ft) |
| Propellant mass | 54,000 kg (120,000 lb) |
| Powered by | 2 × RL10C |
| Maximum thrust | 212 kN (48,000 lbf) |
| Specific impulse | 453.8 s (4.450 km/s) |
| Burn time | 1,077 seconds |
| Propellant | LOX / LH2 |
The Centaur is a family of rocket propelled upper stages that has been in use since 1962. It is currently produced by U.S. launch service provider United Launch Alliance, with one main active version and one version under development. The 3.05 m (10 ft) diameter Common Centaur/Centaur III flies as the upper stage of the Atlas V launch vehicle, and the 5.4 m (18 ft) diameter Centaur V has been developed as the upper stage of ULA's new Vulcan rocket. Centaur was the first rocket stage to use liquid hydrogen (LH2) and liquid oxygen (LOX) propellants, a high-energy combination that is ideal for upper stages but has significant handling difficulties.