Saturn II

There was a large payload gap between the Saturn IB's {{convert|46000|lb|kg|adj=on}} low Earth orbit capacity and the Saturn V's {{convert|310000|lb|kg|adj=on}} capability.

In the mid-1960s NASA's Marshall Space Flight Center (MSFC) initiated several studies to extend the capabilities of the Saturn family. NASA specified a LEO of {{convert|185|km|nmi|order=flip}}, 28° inclination for payload calculations, and the studies examined a number of Modified Launch Vehicle (MLV) configurations based on the Saturn IB and Saturn V launch vehicles as well as Intermediate Payload (INT) launch vehicles based on modified Saturn V stages (MS-IC, MS-II, and MS-IVB).

Martin Marietta (builder of Atlas and Titan rockets), Boeing (builder of S-IC first stages), and North American Aviation (builder of the S-II second stage) were three of the companies that provided responses.

North American believed the best way to fill the gap was to use the Saturn V's second stage, the S-II, as the first stage of an intermediate launch vehicle. The basic concept of the Saturn II was to save money by ceasing production of the Saturn IB rocket, and replacing it with launch vehicles built entirely with current Saturn V components. This would allow closing down Chrysler Space Division production lines for the S-IB first stage, and would allow for more efficient integration of rocket systems.

The baseline for the Saturn II was a Saturn V, without the Boeing-built S-IC first stage. The Saturn V's second stage S-II became the first stage, and the non-restartable S-IVB-200 used on the Saturn IB became the second stage. Such a vehicle could not fly without modification, because the S-II was designed to operate in the near-vacuum of high altitude space. Atmospheric thrust suppression reduced the five Rocketdyne J-2 engines' {{convert|1000000|lbf|kN}} of vacuum thrust to {{convert|546500|lbf|kN}} at sea level,{{Cite web |title=J-2 |url=http://www.astronautix.com/j/j-2.html |access-date=2024-01-18 |website=www.astronautix.com}} insufficient to lift the {{convert|1364900|lb|kg|adj=on}} weight of the two stages off of the ground, even without a payload. This required that the S-II be either refit with higher thrust engines, augmented with solid rocket boosters, or both. Another design variable was the amount of the full {{convert|1005500|lb|kg}} propellant load carried in the S-II, and {{convert|241300|lb|kg}} in the S-IVB stage.

Before any version could be put into production, work on all Saturn variants was stopped in favor of launching all future payloads from the Space Shuttle.

The Saturn INT-17 was the first version of the Saturn II to be considered. It replaced the first stage's five J-2 engines with seven higher thrust HG-3-SL engines, giving {{convert|1334000|lbf|kN}} of sea level thrust. It would burn a reduced S-II propellant load of {{convert|986000|lb|kg}} in 200 seconds. The vehicle had a LEO payload capability of {{convert|92000|lb|kg}} with a gross weight of {{convert|1112000|lb|kg}}. The reduced payload permitted a savings of {{convert|300|kg|lb|order=flip}} in structural weight, and omitting the S-IVB restart capability saved {{convert|700|kg|lb|order=flip}}.{{Cite web |title=Saturn INT-17 |url=http://www.astronautix.com/s/saturnint-17.html |access-date=2024-01-18 |website=www.astronautix.com}}

This configuration was dropped when it was determined that the HG-3-SL could not compete with the J-2 in terms of overall performance, reliability, and cost-effectiveness. This required the addition of booster stages in order to provide more takeoff thrust.

The Saturn INT-18 would have used the standard S-II with J-2 engines, augmented by two or four Titan SRBs. The UA1204 and UA1207 boosters were considered, with the highest total impulse configuration using four UA1207 boosters, capable of placing {{convert|146,000|lb|kg}} of payload into low Earth orbit. Designers considered changing the amount of fuel loaded into the rocket, and whether to ignite the S-II stage on the ground, or whether to launch using the solids, and start the main stage in flight. Two versions omitted the S-IVB stage.

The following configurations were studied:{{Cite web |title=Saturn INT-18 |url=http://www.astronautix.com/s/saturnint-18.html |access-date=2024-01-18 |website=www.astronautix.com}}

The Saturn INT-19 would have used smaller solid boosters, derived from the first stage of the Minuteman missile, to supplement the thrust of the S-II. Eleven configurations were studied, using between four and twelve solids, with some being started at lift-off, and some being started in flight, and varying propellant loads in the Saturn stages. The S-II stage would have been modified by refitting the J-2–SL engines with reduced expansion ratio nozzles, to increase sea level thrust to {{convert|174400|lbf|kN}} per engine. The highest total impulse configuration would have used twelve boosters, with eight started at launch and four started after the first group had been jettisoned. It would have been capable of lofting a payload of {{convert|34200|kg|lb|order=flip}}.

The following configurations were studied:{{Cite web |title=Saturn INT-19 |url=http://www.astronautix.com/s/saturnint-19.html |access-date=2024-01-18 |website=www.astronautix.com}}

• Apollo Applications Program
• Saturn INT-20
• Saturn INT-21

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{{reflist}}{{Saturns}}

Category:Saturn II