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The Saturn V [f] is a retired ... The instrument unit for the Apollo 4 Saturn V. The Saturn V's instrument unit was built by IBM and was placed on top of the rocket's ...
Three versions were built and flown: the medium-lift Saturn I, the heavy-lift Saturn IB, and the super heavy-lift Saturn V. Von Braun proposed the Saturn name in October 1958 as a logical successor to the Jupiter series as well as the Roman god 's powerful position.
The F-1 is a rocket engine developed by Rocketdyne.The engine uses a gas-generator cycle developed in the United States in the late 1950s and was used in the Saturn V rocket in the 1960s and early 1970s.
During the Space Race, the Saturn V and N1 were built by the United States and Soviet Union, respectively. After the Saturn V's successful Apollo program and the N1's failures, the Soviets' Energia launched twice in the 1980s, once bearing the Buran spaceplane.
The Saturn V rocket was used in the Apollo program to depart Earth's gravity. S-IC-T, like all following Saturn V's S-IC rockets used five Rocketdyne F-1 engines. The Rocketdyne F-1 engine was first tested in March 1959 and delivered to NASA in October 1963. S-IC-T was built starting in 1963 and complete in 1965.
It came under the management of NASA in 1961, and was used for the construction of the S-IC first stage of the Saturn V rockets and the S-IB first stage of the Saturn IB rockets built by Chrysler Corporation. It is home to the first stage of the last-constructed Saturn V, SA-515, built by The Boeing Company.
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 1,000,000 pounds-force (4.4 MN) of thrust.
The S-IC (pronounced S-one-C [3] [4]) was the first stage of the American Saturn V rocket. The S-IC stage was manufactured by the Boeing Company. Like the first stages of most rockets, more than 90% of the mass at launch was propellant, in this case RP-1 rocket fuel and liquid oxygen (LOX) oxidizer.