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Saturn A-2

From Wikipedia, the free encyclopedia
Saturn A-2
FunctionUncrewed launch vehicle
ManufacturerVon Braun
Country of originUnited States
Size
Height62 m (203.00 ft)
Diameter6.52 m (21.39 ft)
Mass524,484 kg
Stages3 (all used on various vehicles, now retired)
Launch history
StatusNever flown
Launch sitesN/A
First stage - S-IB
Engines8 × Rocketdyne H-1
Thrust1,600,000 lbf (7,100 kN)
Burn time150 seconds
PropellantRP-1/LOX
Second stage Jupiter Cluster
Engines4 x Rocketdyne LR79
Thrust3,034.285 kN
Burn time172 seconds
PropellantRP-1/LOX
Third stage - Centaur C
Engines2 RL-10A-1
Thrust133 kN
Burn time430 seconds
PropellantLH2

Studied with the Saturn A-1 in 1959, the Saturn A-2 was deemed more powerful than the Saturn I rocket, consisting of a S-IB first stage, which actually flew on the Saturn IB, a second stage which contains four S-3 engines that flew on the Jupiter IRBM and a Centaur high-energy liquid-fueled third stage.[1]

References

[edit]
  1. ^ "Saturn A-2". www.astronautix.com. Archived from the original on December 28, 2016.
  • Koelle, Heinz Hermann, Handbook of Astronautical Engineering, McGraw-Hill, New York, 1961.
  • Bilstein, Roger E, Stages to Saturn, US Government Printing Office, 1980. ISBN 0-16-048909-1.