Saturn I
The Saturn I was a rocket designed as the United States' first medium lift launch vehicle for up to 20,000-pound (9,100 kg) low Earth orbit payloads. The rocket's first stage was built as a cluster of propellant tanks engineered from older rocket tank designs, leading critics to jokingly refer to it as "Cluster's Last Stand". Its development was taken over from the Advanced Research Projects Agency in 1958 by the newly formed civilian NASA. Its design proved sound and flexible. It was successful in initiating the development of liquid hydrogen-fueled rocket propulsion, launching the Pegasus satellites, and flight verification of the Apollo command and service module launch phase aerodynamics. Ten Saturn I rockets were flown before it was replaced by the heavy lift derivative Saturn IB, which used a larger, higher total impulse second stage and an improved guidance and control system. It also led the way to development of the super-heavy lift Saturn V which carried the first men to landings on the Moon in the Apollo program.
The first Saturn I was launched October 27, 1961. | |
Function | Large booster technology Large scientific satellite payloads in LEO Apollo spacecraft development |
---|---|
Manufacturer | Chrysler (S-I) Douglas (S-IV) Convair (S-V) |
Country of origin | United States |
Size | |
Height | 180 ft (55 m) |
Diameter | 21 ft 8 in (6.60 m) |
Mass | 1,124,000 lb (510,000 kg) |
Stages | 2 or 3 (3rd stage flew, but never in an active configuration) |
Capacity | |
Payload to 185 km Circular Low Earth orbit, 28° tilt | |
Mass | 20,000 lb (9,100 kg) (2 stages) |
Payload to TLI | |
Mass | 4,900 lb (2,220 kg) (2 stages) |
Launch history | |
Status | Retired |
Launch sites | Cape Canaveral, LC-37 and LC-34 |
Total launches | 10 |
Success(es) | 10 |
Failure(s) | 0 |
First flight | October 27, 1961 |
Last flight | July 30, 1965 |
Type of passengers/cargo | Boilerplate Apollo CM, Pegasus |
First stage – S-I | |
Powered by | 8 H-1 |
Maximum thrust | 1,500,000 lbf (6.7 MN) |
Propellant | RP-1 / LOX |
Second stage – S-IV | |
Powered by | 6 RL10 |
Maximum thrust | 90,000 lbf (400 kN) |
Propellant | LH2 / LOX |
Third stage – S-V - Flew inactively | |
Powered by | 2 RL10 |
Maximum thrust | 133 kN (30,000 lbf) |
Propellant | LH2 / LOX |
President John F. Kennedy identified the Saturn I, and the SA-5 launch in particular, as being the point where US lift capability would surpass the Soviets, after being behind since Sputnik.