Saturn A-1

From Wikipedia, the free encyclopedia
Jump to: navigation, search
Saturn A-1
Function Unmanned launch vehicle
Manufacturer Von Braun
Country of origin United States
Height 49.62 m (162.29 ft)
Diameter 6.52 m (21.39 ft)
Mass 524,484 kg
Stages 3 (all used on various vehicles, now retired)
Launch history
Status Never flown
Launch sites N/A
First stage - S-I
Engines 8 H-1
Thrust 7,582 kN
Burn time 150 seconds
Fuel RP-1/LOX
Second stage - Titan I
Engines 2 LR-87-3
Thrust 1,467 kN
Burn time 138 seconds
Fuel RP-1/LOX
Third stage - Centaur C
Engines 2 RL-10A-1
Thrust 133 kN
Burn time 430 seconds
Fuel LH2/LOX

Saturn A-1, studied in 1959, was projected to be the first version of Saturn I and was to be used if necessary before the S-IV liquid hydrogen second stage became available. The first stage, proposed for the Juno V rocket, but finally used for the first Saturn rocket, would propel the Saturn A-1 into space, with the first stage of a Titan I missile continuing the flight and finally, a Centaur C high-energy double-engine third stage could perform a small burn to send a payload into its final orbit, or it can perform a big burn to take a payload out of Earth orbit to other planets. This rocket never flew, but all stages of the Saturn A-1 were used on different launch vehicles. Today, they are all retired.