S-II

Image:Saturn v building seal beach.jpg

The beginning of the S-II came in December 1959 when a committee recommended the design and construction of a high-thrust, liquid hydrogen fueled engine. The contract for this engine was given to Rocketdyne and it would be later called the J-2. At the same time the S-II stage design began to take shape. Initially it was to have four J-2 engines and be {{convert|74|ft|m}} in length and {{convert|260|in|m}} in diameter.

In 1961 the Marshall Space Flight Center began the process to find the contractor to build the stage. Out of the 30 aerospace companies invited to a conference where the initial requirements were laid out, only seven submitted proposals a month later. Three of these were eliminated after their proposals had been investigated. However it was then decided that the initial specifications for the entire rocket were too small and so it was decided to increase the size of the stages used. This raised difficulties for the four remaining companies as NASA had still not yet decided on various aspects of the stage including size, and the upper stages that would be placed on top.

On September 11, 1961, the contract was awarded to North American Aviation (who were also awarded the contract for the Apollo Command/Service Module), with the manufacturing plant built by the government at Seal Beach, California.{{Cite book|last=Aikens|first=David|url=https://history.nasa.gov/MHR-5/part-2.htm|title="Saturn Illustrated Chronology - Part 2: January 1961 through December 1961"|date=15 May 1965 |publisher=NASA-Marshall Space Flight Center|pages=28}} 15 flight stages were to be produced.

Plans were also developed to build 10 follow-on stages, S-II-16 through -25, but funding to assemble them never materialized.{{Cite web|title=Manufacturing plan for Saturn S-II, Stages 16-25|url=http://libarchstor2.uah.edu/digitalcollections/items/show/11131|access-date=2023-03-18|website=uah.edu|date=14 June 1967 }} These stages would have supported later Apollo missions, including those of the Apollo Applications Program.

Image:SaturnV S-II.jpg When fully loaded with propellant, the S-II had a mass of about {{cvt|480|t|lb}}. The hardware was only 7.6% of this—92.4% was liquid hydrogen and liquid oxygen.[https://history.nasa.gov/SP-4029/Apollo_18-19_Ground_Ignition_Weights.htm Apollo 18-19 Ground Ignition Weights] (NASA)

At the bottom was the thrust structure supporting five J-2 engines in a quincunx arrangement. The center engine was fixed, while the other four were gimballed, similar to the engines on the S-IC stage below.

Instead of using an intertank (empty container between tanks) like the S-IC, the S-II used a common bulkhead (similar to that of the S-IV and S-IVB stages) that included both the top of the LOX tank and bottom of the LH2 tank. It consisted of two aluminum sheets separated by a honeycomb structure made of phenolic resin. It insulated a {{convert|126|F-change|adj=on}} temperature differential between the two tanks. The use of a common bulkhead saved 3.6 tonnes in weight, both by eliminating one bulkhead and by reducing the overall length of the stage. The S-II's common bulkhead design was tested in 1965 on the subscale Common Bulkhead Test Tank (CBTT), made of only 2 LH2 tank cylinders.

The LOX tank was an ellipsoidal container of 10 meters diameter and 6.7 meters high holding up to {{convert|83,000|USgal|m3}} or {{convert|789,000|lb|t}} of oxidizer.{{cite web|url=http://history.msfc.nasa.gov/saturn_apollo/documents/Second_Stage.pdf|title=Second Stage Fact Sheet|access-date=2014-09-23|archive-url=https://web.archive.org/web/20150326211327/http://history.msfc.nasa.gov/saturn_apollo/documents/Second_Stage.pdf|archive-date=2015-03-26|url-status=dead}} It was formed by welding 12 gores (large triangular sections) and two circular pieces for the top and bottom. The gores were shaped by positioning in a 211,000-liter tank of water with three carefully orchestrated sets of underwater explosions to shape each gore.

The LH2 tank was constructed of six cylinders: five were 2.4 meters high and the sixth was 0.69 meters high. The biggest challenge was the insulation. Liquid hydrogen must be kept colder than about 20 °C above absolute zero ({{convert|-423|F|K C|disp=or}}) so good insulation is very important. Initial attempts did not work well: there were bonding issues and air pockets. Initially, the stage was insulated with a honeycomb material. These panels had grooves milled in the back which were purged with helium during filling. The final method was to spray insulation on by hand and trim the excess. This change saved both weight and time and avoided the issues with air pockets entirely. The LH2 tank volume was {{convert|260,000|USgal|m3}} for storing {{convert|153,000|lb|t}} of liquid hydrogen.

The S-II was constructed vertically to aid welding and keep the large circular sections in the correct shape.

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• S-IC
• S-IVB
• Apollo (spacecraft)
• MS-II

{{reflist}}

• {{cite book|first=Roger E.|last=Bilstein|year=1980|url=https://history.nasa.gov/SP-4206/sp4206.htm |title=Stages to Saturn: A Technological History of the Apollo/Saturn Launch Vehicles|publisher=NASA|series=NASA History Series SP-4206}}
• [http://www.apollosaturn.com/ Apollo Saturn Reference Page]

{{J-2 (rocket engine)}}

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Category:Apollo program

Category:Rocket stages

Category:Saturn V