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Saturn A-2

Function	Uncrewed launch vehicle
Manufacturer	Von Braun
Country of origin	United States
Size
Height	62 m (203.00 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-IB
Engines	8 × Rocketdyne H-1
Thrust	1,600,000 lbf (7,100 kN)
Burn time	150 seconds
Propellant	RP-1/LOX
Second stage Jupiter Cluster
Engines	4 x Rocketdyne LR79
Thrust	3,034.285 kN
Burn time	172 seconds
Propellant	RP-1/LOX
Third stage - Centaur C
Engines	2 RL-10A-1
Thrust	133 kN
Burn time	430 seconds
Propellant	LH2
[edit on Wikidata]

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.

References

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.

v t e Saturn launch vehicle family
Early proposals	Juno V Saturn A-1 A-2 B-1
"C" series	Saturn C-1 C-2 C-3 C-4 C-5 C-5N C-8
Saturn I series	Saturn I IB IB-CE IB-A IB-B IB-C IB-D INT-05 INT-11 INT-12 INT-13 INT-14 INT-15 INT-16 INT-27 LCB
Saturn II series	Saturn II INT-17 INT-18 INT-19
Saturn V series	Saturn V MLV V ELV INT-20 INT-21 INT-23 INT-24 INT-25 Saturn-Shuttle Saturn V-3 V-A V-B V-C V-D V-Centaur Jarvis

• Cancelled space launch vehicles
• Saturn A