Saturn C-3 - Variants and Derivatives

Variants and Derivatives

Since 1961 a number of variants of the Saturn C-3 have been studied, proposed, and funded. The common theme of these variants is the usage of two or three Rocketdyne F-1 engines in a S-IB-2 or S-1C stage with diameters ranging from 8 to 10 meters (27 to 33 feet) that could lift 45,000 to 50,000 kg to Low Earth Orbit (LEO).

The lack of a Saturn C-3 launch vehicle in 1965 created a large payload gap between the Saturn IB's 19,000 kg low-earth orbit capacity and the two-stage Saturn V's 100,000 kg capability. In the mid-1960s NASA's Marshall Space Flight Center (MSFC) initiated several studies to fill this payload capacity gap and to extend the capabilities of the Saturn family. Three companies provided proposals to MSFC for this requirement. Martin Marietta (builder of Atlas, Titan vehicles), Boeing (builder of S-1B and S-1C first stages) and North American (builder of the S-II second stage).

The 1986 Challenger disaster and 2010 Space Launch System resulted in Saturn C-3 derivative proposals using the Rocketdyne F-1A engines with existing booster core diameters and tooling (S-IC, Space Shuttle external tank, Delta IV Common Booster Core).

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