Saturn II
Stage · USA
Original archive entry. The text, images and links below are kept as they were written.

Credit: © Mark Wade
LOx/LH2 propellant rocket stage. Configuration as flown.
Cost $ : 290.000 million. No Engines: 5.
Subtopics
- 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.
Related
- 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

