Saturn A-1

Saturn A-1

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)
Capacity
Payload to low Earth orbit
Mass	13,600 kg (30,000 lb)
for LEO
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
[edit on Wikidata]

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

• S-I
• Saturn I
• Juno V
• Titan I
• Centaur

References

• Project Horizon Report: Volume I, Summary and Supporting Considerations (PDF). United States Army. June 9, 1959.
• Project Horizon Report: Volume II, Technical Considerations & Plans (PDF). United States Army. June 9, 1959.

This page was last edited on 27 May 2024, at 23:33