S-II

The S-II (pronounced "S-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 quincunx pattern. The second stage accelerated the Saturn V through the upper atmosphere with of thrust.

Key facts

Rocket/stage.engines: 5×J-2
Rocket stage.image: ap6-MSFC-6758331.jpg
Rocket stage.caption: The Apollo 6 S-II stage during stacking operations in the VAB
Rocket stage.name: S-II
Rocket stage.manufacturer: North American
Rocket stage.country: United States
Rocket stage.rockets: Saturn V
Rocket stage.status: Retired
Rocket stage.launches: 13
Rocket stage.success: 12
Rocket stage.other_outcome: Partial failure (Apollo 6)
Rocket stage.first: November 9, 1967 (Apollo 4)
Rocket stage.last: May 14, 1973 (Skylab 1)
Rocket/stage.name: Specifications
Rocket/stage.burntime: 367 seconds
Rocket/stage.fuel: LH2 / LOX

via Wikipedia infobox

Wikidata facts

Diameter: 10.06
Mass: 72001
Image: Ap6-MSFC-6758331 (cropped).jpg
Height: 24.84

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Commons category: Saturn S-II
maximum thrust: 1150000

Sources (5)

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Article

19 sections

Contents

History
Configuration
Stages built
Proposed variants
Saturn S-II-4
Saturn S-II-8
Saturn S-II-C3
Saturn II C-5A
Saturn MS-II-1
Saturn MS-II-1-J-2T-200K
Saturn II-INT-17
Saturn II-SL
Saturn MS-II-1A
Saturn MS-II-2
Saturn MS-II-1-J-2T-250K
Saturn MS-II-3B
Saturn MS-II-4(S)B
See also
References

==History== left|thumb|200px|S-II assembly building in Seal Beach, CA 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 in length and in diameter.