Country of origin | United States |
---|---|
Used on |
Saturn C-2 (stage 2) Saturn C-3 (stage 3) |
General characteristics | |
Diameter | 27 ft (8.2 m) |
S-III | |
Powered by | 2 J-2 engine |
Maximum thrust | 400,000 lbf (1.8 MN) |
Propellant | LOX/ LH2 |
The S-III (pronounced "S 3") was a proposed third stage of the early Saturn C designs for a five-stage Saturn launch vehicle. The Saturn C configurations were based on a "building block" approach, in which the upper stages would be test-flown before the intermediate stages. The S-III was to have been fueled with liquid oxygen and liquid hydrogen and powered by two J-2 engines. The original Saturn C-2 design would have been a three- or four-stage launch vehicle using the S-I plus S-III plus S-IV stages plus, for some missions, S-V.
This article incorporates public domain material from websites or documents of the National Aeronautics and Space Administration.
Country of origin | United States |
---|---|
Used on |
Saturn C-2 (stage 2) Saturn C-3 (stage 3) |
General characteristics | |
Diameter | 27 ft (8.2 m) |
S-III | |
Powered by | 2 J-2 engine |
Maximum thrust | 400,000 lbf (1.8 MN) |
Propellant | LOX/ LH2 |
The S-III (pronounced "S 3") was a proposed third stage of the early Saturn C designs for a five-stage Saturn launch vehicle. The Saturn C configurations were based on a "building block" approach, in which the upper stages would be test-flown before the intermediate stages. The S-III was to have been fueled with liquid oxygen and liquid hydrogen and powered by two J-2 engines. The original Saturn C-2 design would have been a three- or four-stage launch vehicle using the S-I plus S-III plus S-IV stages plus, for some missions, S-V.
This article incorporates public domain material from websites or documents of the National Aeronautics and Space Administration.