S-II

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S-II

The Apollo 6 S-II stage during stacking operations in the VAB
Fact sheet
Height	24.9 m (82 ft)
Diameter	10 m (33 ft)
Mass	480,000 kg (1,060,000 lb)
Engines	5 J-2 engines
Thrust	5,115 kN (1,150,000 lbf)
Burn time	367 s
Fuel	liquid hydrogen and liquid oxygen

The S-II (pronounced "ess two") was the second stage of the Saturn V rocket. It was built by North American Aviation. Using liquid hydrogen (LH2) and liquid oxygen (LOX) it had five J-2 engines in a cross pattern. The second stage accelerated the Saturn V through the upper atmosphere with 5 MN of thrust.

Contents 1 History 2 Configuration 3 Stages Built 4 References

[edit] History

The beginning of the S-II came in December of 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 22.5 meters in length and 6.5 meters 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 7 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.

In the end on 11 September 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.

[edit] Configuration

When fully loaded with fuel, the S-II had a mass of about 500,000 kg. The hardware was only 3% of this—97% was liquid hydrogen and liquid oxygen.

At the bottom was the thrust structure supporting five J-2 engines. The center engine was fixed, while the other four were gimballed.

Instead of using an intertank (empty container between tanks) like the S-IC, the S-II used a common bulkhead that included both the top of the LOX tank and bottom of the LH2 tank. It consisted of two aluminium sheets separated by a honeycomb structure made of phenol. It insulated a 70 °C (125 °F) temperature differential between the two tanks. The use of a common bulkhead saved 3.6 tonnes in weight.

The LOX tank was an ellipsoidal container of 10 meters diameter and 6.7 meters high. 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 0.69 meter high. The biggest challenge was the insulation. Liquid hydrogen must be kept colder than about 20 °C above absolute zero (20 K or −252 °C or −423 °F) so good insulation is very important. Initial attempts did not work well: there were bonding issues and air pockets. The final method was to spray insulation on by hand and trim the excess.

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

[edit] Stages Built

Serial number	Use	Launch date	Current location	Notes
S-II-F	Used as Dynamic Test Stage replacement after destruction of S-II-S/D and S-II-T		At the U.S. Space & Rocket Center, Huntsville, Alabama
S-II-T				Destroyed in explosion May 28, 1966
S-II-D	Construction cancelled
S-II-S/D	Structural and Dynamic Test Vehicle			Destroyed in test stand September 29, 1965
S-II-1	Apollo 4	November 9, 1967	32°12′N, 39°40′W	Carried "Camera Targets" spaced around the forward skirt and carried cameras to record first stage separation
S-II-2	Apollo 6	April 4, 1968		carried cameras to record first stage separation
S-II-3	Apollo 8	December 21, 1968	31°50′N, 37°60′W
S-II-4	Apollo 9	March 3, 1969	31°28′N, 34°2′W	1800 kg lighter allowing 600 kg more payload, larger engines and carried more LOX
S-II-5	Apollo 10	May 18, 1969	31°31′N, 34°31′W
S-II-6	Apollo 11	July 16, 1969	31°32′N, 34°51′W
S-II-7	Apollo 12	November 14, 1969	31°28′N, 34°13′W
S-II-8	Apollo 13	April 11, 1970	32°19′N, 33°17′W	Inboard engine failed during ascent due to pogo oscillations.
S-II-9	Apollo 14	January 31, 1971
S-II-10	Apollo 15	July 26, 1971
S-II-11	Apollo 16	April 16, 1972
S-II-12	Apollo 17	December 7, 1972
S-II-13	Skylab 1	May 14, 1973		Modified to act as the terminal stage
S-II-14	Apollo 18 (cancelled)	N/A	Apollo-Saturn V Center, Kennedy Space Center	From the cancelled Apollo 18 mission.
S-II-15	Skylab 1 backup (not flown)	N/A	Johnson Space Center	From SA-515 the Skylab backup vehicle which NASA did not use.

[edit] References

• Stages to Saturn
• Apollo Saturn Reference Page

v • d • e  J-2 Rocket Engine
	Main Article: J-2		Technologies: Bipropellant | Gas-generator cycle | LOX | LH2
	Historic Spacecraft: Saturn IB (S-IVB) | Saturn V (S-II, S-IVB)
	Future Spacecraft: Ares I | Ares IV | Ares V | Earth Departure Stage
	Other LOX & LH2 Engines: SSME | RS-68 | RL-10 | Vulcain