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 originUnited States
Used onSaturn MLV
General characteristics
Height25.88 m (84.9 ft)
Diameter10.06 m (33.0 ft)
Gross mass521,447 kg (1,149,594 lb)
Propellant mass471,570 kg (1,039,630 lb)
Empty mass49,877 kg (109,960 lb)
Derived fromS-II
Launch history
StatusCancelled
Engines
Powered by5 J-2s
Maximum thrust1,033 kN (232,000 lbf)
Specific impulse425 seconds (4.17 km/s)
Burn time361 s
PropellantLH2/LOX

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