Atlas-Centaur
Description
The Atlas-Centaur was a US expendable launch vehicle derived from the SM-65 Atlas D missile. Convair, the manufacturer of the Atlas, developed the Centaur upper stage specifically for that booster, sharing its pressure stabilized tank structure. Centaur was the first rocket stage to utilize liquid hydrogen (LH2) and liquid oxygen (LOX) as propellants. Despite high performance, LH2 had to be chilled at extremely low temperatures (lower than LOX) and its low density meant that large fuel tanks were needed.
Missions
68
Success Rate
83.8%
Successes
55
Failures
9
Success Streak
1
Partial Failures
4
Previous
FLTSATCOM-8 (USA-46)
FLTSATCOM-6
Configurations
Atlas-SLV3D Centaur-D1AR
Active 1975 to 1983
Stages
2
Atlas-SLV3D Centaur-D1A
Active 1973 to 1975
Stages
2
Atlas-SLV3C Centaur-D
Active 1967 to 1972
Stages
2
Atlas-LV3C Centaur-D
Active 1965 to 1967
Stages
2
Atlas-LV3C Centaur-C
Active 1964 to 1965
Stages
2
Atlas-LV3C Centaur-B
Active in 1963
Stages
2
Atlas-LV3C Centaur-A
Active in 1962
Stages
2
Atlas-G Centaur-D1AR
Active 1984 to 1989
Payload to Orbit
LEO: 5,900 kg
GTO: 2,222 kg
Stages
2