Vehicle configurations representative of several alternative uprating methods were specified by the Marshall Space Flight Center for initial studies.
- Thrust uprating and modifying of the five F-1 rocket engines used in the first S-IC stage, and corresponding increases in propellant tank capacities.
- Addition of a sixth F-1 engine in the S-IC stage, as an alternative to engine uprating, plus increased propellant capacities.
- Use of solid rocket motor boosters derived from the Titan IIIC vehicle.
- Additional J-2 engines in the S-II stage, ~131 s increased upper stage propellant capacities.
- Improved or advanced upper stage engines, such as the HG-3 (rocket engine), plus increased propellant capacities.
The baseline Saturn MLV would incorporate these changes from the Saturn V vehicle. Saturn IC (first stage) stretched 240 inches with 5.6 million pounds propellant and 5 new F-1A engines; S-II (second stage) stretched 41 inches with 1.0 million pounds propellant and 5 J-2 engines; S-IVB (third stage) strengthened, but with standard 230,000 lbs propellant, 1 J-2 engine.
|1st Stage||2nd Stage||3rd Stage||LEO Payload|
*) Indicates zero stage strap on boosters. In both cases 4x-Titan UA-1205
-  "Modified Launch Vehicle (MLV) Saturn V Improvement Study Composite Summary Report", NASA Marshall Space Flight Center (MSFC), July 1965, 76 pages. Improved Saturn V configurations studied under contract NAS8-11359.
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