The MS-II was a proposed further development of the S-II rocket stage developed by North American Aviation.
Country of origin | United States |
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Used on | Saturn MLV |
General characteristics | |
Height | 25.88 m (84.9 ft) |
Diameter | 10.06 m (33.0 ft) |
Gross mass | 521,447 kg (1,149,594 lb) |
Propellant mass | 471,570 kg (1,039,630 lb) |
Empty mass | 49,877 kg (109,960 lb) |
Derived from | S-II |
Launch history | |
Status | Cancelled |
Engines | |
Powered by | 5 J-2s |
Maximum thrust | 1,033 kN (232,000 lbf) |
Specific impulse | 425 seconds (4.17 km/s) |
Burn time | 361 s |
Propellant | LH2/LOX |
External links
Attribution:
- This article incorporates public domain material from websites or documents of the National Aeronautics and Space Administration.
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