MS-II

Not to be confused with MS-2.

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The MS-II was a proposed further development of the S-II rocket stage developed by North American Aviation.

MS-II

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]

* astronautix.com (Saturn MS-II-1-J-2T-200K)
* astronautix.com (Saturn MS-II-1)

Attribution:

* This article incorporates public domain material from websites or documents of the National Aeronautics and Space Administration.

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