Jump to content

Saturn A-1

From Wikipedia, the free encyclopedia

Saturn A-1
FunctionUncrewed launch vehicle
ManufacturerVon Braun
Country of originUnited States
Size
Height49.62 m (162.29 ft)
Diameter6.52 m (21.39 ft)
Mass524,484 kg
Stages3 (all used on various vehicles, now retired)
Capacity
Payload to low Earth orbit
Mass13,600 kg (30,000 lb)
for LEO
Launch history
StatusNever flown
Launch sitesN/A
First stage - S-I
Engines8 H-1
Thrust7,582 kN
Burn time150 seconds
PropellantRP-1/LOX
Second stage Titan I
Engines2 LR-87-3
Thrust1,467 kN
Burn time138 seconds
PropellantRP-1/LOX
Third stage - Centaur C
Engines2 RL-10A-1
Thrust133 kN
Burn time430 seconds
PropellantLH2 / 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.[1]

It was designed as a three stage vehicle. The S-I first stage (initially proposed for the Juno V rocket and eventually used on Saturn I) would propel the Saturn A-1 into space, continuing the flight with a Titan I[2]: 3–6  missile based second stage. Finally a Centaur[2]: 3–6  C high-energy double-engine third stage could send a payload into its final Earth orbit or to other planets.

The Saturn A-1 never flew, but all proposed stages were used on different launch vehicles. Today, they are all retired.

See also

[edit]

References

[edit]
  1. ^ "Saturn A-1". November 14, 2016. Archived from the original on November 14, 2016. Retrieved May 27, 2024.
  2. ^ a b Lunar Exploration with Saturn-Boosted Systems (PDF) (Technical report). Army Ballistic Missile Agency. October 1, 1959. Archived (PDF) from the original on May 31, 2023. Retrieved May 31, 2023.