MS-II
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The MS-II was a proposed further development of the S-II rocket stage developed by North American Aviation.
 Diagram of the MS-II rocket stage | |
| Country of origin | United States |
|---|---|
| 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[edit]
Attribution:
This article incorporates public domain material from websites or documents of the National Aeronautics and Space Administration.
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