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https://en.wikipedia.org/wiki/Centaur_(rocket_stage) 
 
Centaur III
Centaur upper stage of Atlas V rocket.jpg
A single-engine Centaur III being raised for mating to an Atlas V rocket
ManufacturerUnited Launch Alliance
Used onAtlas V- Centaur III
Vulcan- Centaur V
General characteristics
Height12.68 m (499 in)
Diameter3.05 m (120 in)
Gross mass2,247 kg (4,954 lb) (single engine)
2,462 kg (5,428 lb) (dual engine)
Propellant mass20,830 kg (45,920 lb)
Associated stages
DerivativesCentaur V
Advanced Common Evolved Stage
Launch history
StatusActive
Total launches245 as of January 2018
First flightMay 9, 1962
Centaur III
Engines1 or 2 RL10
Thrust99.2 kN (22,300 lbf) (per engine)
Specific impulse450.5 sec
Burn timeVariable
FuelLiquid oxygen and liquid hydrogen

The Centaur is a family of rocket propelled upper stages currently produced by U.S. launch service provider United Launch Alliance, with one main active version and one version under development. The 3.8 m diameter Common Centaur/Centaur III (as referenced in the infobox) flies as the upper stage of the Atlas V launch vehicle, while the 5.4 m diameter Centaur V is being 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.

Characteristics