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Saturn II
Saturn II stage
Credit: © Mark Wade
Status: Flown 1968. Thrust: 5,165.79 kN (1,161,316 lbf). Gross mass: 490,778 kg (1,081,980 lb). Unfuelled mass: 39,048 kg (86,086 lb). Specific impulse: 421 s. Specific impulse sea level: 200 s. Burn time: 390 s. Height: 24.84 m (81.49 ft). Diameter: 10.06 m (33.00 ft). Span: 10.06 m (33.00 ft).
Cost $ : 290.000 million. No Engines: 5.
| Saturn S-II LOx/LH2 propellant rocket stage. Early design version for use with Saturn I first stage. |
| Saturn S-II-4 LOx/LH2 propellant rocket stage. Version for Saturn C-4. |
| Saturn S-II-8 LOx/LH2 propellant rocket stage. Version for Saturn C-8. |
| Saturn S-II-C3 LOx/LH2 propellant rocket stage. Version for Saturn C-3. |
| Saturn II C-5A LOx/LH2 propellant rocket stage. Final common second stage design for Saturn C-3, C-4 and C-5 (November 1961). Developed into Saturn V second stage. |
| Saturn MS-II-1 LOx/LH2 propellant rocket stage. Basic Saturn II with 41 inch stretch of hydrogen tank. |
| Saturn MS-II-1-J-2T-200K LOx/LH2 propellant rocket stage. Basic Saturn II with 41 inch stretch of hydrogen tank, uprated J-2T 200k engines with 10 second increase in specific impulse. |
| Saturn II-INT-17 LOx/LH2 propellant rocket stage. Saturn II modified with reduced expansion ratio HG-3 high pressure engines for use a first stage (sea level launch). |
| Saturn II-SL LOx/LH2 propellant rocket stage. Saturn II modified with reduced expansion ratio J-2 engines for use a first stage (sea level launch). Requires solid rocket motor augmentation to get off the ground. |
| Saturn MS-II-1A LOx/LH2 propellant rocket stage. Basic Saturn II with 187 inch stretch of propellant tanks, 1.2 million pound propellant capacity, and 7 J-2 engines. |
| Saturn MS-II-2 LOx/LH2 propellant rocket stage. Basic Saturn II with 187 inch stretch of propellant tanks and high chamber pressure SSME-type engines with 65% increase in thrust and 26 second improvement in specific impulse. |
| Saturn MS-II-1-J-2T-250K LOx/LH2 propellant rocket stage. Basic Saturn II with 41 inch stretch of hydrogen tank, uprated J-2T 250k engines with 25% improvement in thrust and 16 second increase in specific impulse. |
| Saturn MS-II-3B LOx/LH2 propellant rocket stage. S-II with 15.5 foot stretch, 1.29 million pounds propellant, 7 x 400,000 lb thrust toroidal engines. |
| Saturn MS-II-4(S)B LOx/LH2 propellant rocket stage. Standard S-II but with structural strength increased from 86% to 502% depending on station, resulting in 8.6% increase in empty weight. |
Country: USA. Engines: J-2. Launch Vehicles: Saturn V 2, Saturn INT-18, Saturn V, Saturn INT-21, Saturn V-D, Saturn V-Centaur. Propellants: Lox/LH2.
 | Saturn S-2 Geneology Saturn S-II Genealogy Credit: © Mark Wade |
 | Saturn I & II As conceived for Project Horizon, 1958. Credit: © Mark Wade |
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