Engineering:Saturn A-1
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Revision as of 05:32, 5 August 2021 by imported>PolicyEnforcerIA (attribution)
Function | Uncrewed launch vehicle |
---|---|
Manufacturer | Von Braun |
Country of origin | United States |
Size | |
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 |
Propellant | RP-1/LOX |
Second stage Titan I | |
Engines | 2 LR-87-3 |
Thrust | 1,467 kN |
Burn time | 138 seconds |
Propellant | RP-1/LOX |
Third stage - Centaur C | |
Engines | 2 RL-10A-1 |
Thrust | 133 kN |
Burn time | 430 seconds |
Propellant | 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.
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![]() | Original source: https://en.wikipedia.org/wiki/Saturn A-1.
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